NACA 65(2)-215 (naca652215-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(2)-215 (naca652215-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.43 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca652215-il-1000000.txt Download as CSV file: xf-naca652215-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(2)-215
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.7968 0.11670 0.11471 -0.0300 1.0000 0.0127
-17.250 -0.8186 0.10656 0.10445 -0.0360 1.0000 0.0126
-17.000 -0.8785 0.08935 0.08698 -0.0466 1.0000 0.0126
-16.750 -0.9052 0.08026 0.07771 -0.0522 1.0000 0.0126
-16.500 -0.9359 0.07143 0.06869 -0.0572 1.0000 0.0125
-16.000 -0.9669 0.06037 0.05731 -0.0625 1.0000 0.0126
-15.750 -0.9928 0.05415 0.05086 -0.0646 1.0000 0.0127
-15.500 -1.0150 0.04888 0.04537 -0.0656 1.0000 0.0129
-15.250 -1.0223 0.04557 0.04193 -0.0659 1.0000 0.0129
-15.000 -1.0277 0.04259 0.03883 -0.0659 1.0000 0.0131
-14.750 -1.0249 0.04061 0.03681 -0.0658 1.0000 0.0133
-14.500 -1.0242 0.03841 0.03450 -0.0654 1.0000 0.0134
-14.250 -1.0207 0.03656 0.03256 -0.0650 1.0000 0.0135
-14.000 -1.0130 0.03527 0.03124 -0.0646 1.0000 0.0137
-13.750 -1.0083 0.03362 0.02950 -0.0639 1.0000 0.0138
-13.500 -1.0015 0.03227 0.02808 -0.0631 1.0000 0.0141
-13.250 -0.9939 0.03102 0.02675 -0.0622 1.0000 0.0143
-13.000 -0.9846 0.03003 0.02572 -0.0614 1.0000 0.0146
-12.750 -0.9776 0.02852 0.02409 -0.0601 1.0000 0.0147
-12.500 -0.9678 0.02757 0.02305 -0.0590 1.0000 0.0151
-12.250 -0.9579 0.02646 0.02186 -0.0577 1.0000 0.0153
-12.000 -0.9474 0.02549 0.02080 -0.0563 1.0000 0.0155
-11.750 -0.9364 0.02462 0.01985 -0.0548 1.0000 0.0157
-11.500 -0.9117 0.02388 0.01901 -0.0561 0.9807 0.0159
-11.250 -0.8815 0.02149 0.01647 -0.0585 0.9700 0.0164
-11.000 -0.8478 0.02039 0.01531 -0.0614 0.9553 0.0168
-10.750 -0.8249 0.01975 0.01459 -0.0617 0.9349 0.0172
-10.500 -0.8095 0.01933 0.01408 -0.0603 0.9166 0.0176
-10.250 -0.7953 0.01878 0.01343 -0.0586 0.9019 0.0180
-10.000 -0.7811 0.01820 0.01276 -0.0569 0.8892 0.0183
-9.750 -0.7669 0.01764 0.01211 -0.0551 0.8780 0.0186
-9.500 -0.7529 0.01709 0.01147 -0.0531 0.8674 0.0189
-9.250 -0.7377 0.01668 0.01098 -0.0513 0.8580 0.0193
-9.000 -0.7208 0.01630 0.01051 -0.0497 0.8492 0.0195
-8.750 -0.7009 0.01593 0.01008 -0.0487 0.8410 0.0197
-8.250 -0.6723 0.01428 0.00830 -0.0451 0.8251 0.0210
-8.000 -0.6513 0.01393 0.00791 -0.0443 0.8181 0.0216
-7.750 -0.6298 0.01356 0.00750 -0.0435 0.8117 0.0223
-7.500 -0.6082 0.01318 0.00706 -0.0427 0.8049 0.0228
-7.250 -0.5858 0.01285 0.00667 -0.0420 0.7987 0.0235
-7.000 -0.5624 0.01253 0.00632 -0.0415 0.7923 0.0240
-6.750 -0.5398 0.01217 0.00588 -0.0408 0.7862 0.0245
-6.500 -0.5189 0.01162 0.00529 -0.0400 0.7806 0.0258
-6.250 -0.4946 0.01133 0.00497 -0.0396 0.7749 0.0270
-6.000 -0.4698 0.01109 0.00469 -0.0393 0.7696 0.0283
-5.750 -0.4442 0.01086 0.00443 -0.0391 0.7646 0.0294
-5.500 -0.4196 0.01052 0.00405 -0.0387 0.7592 0.0314
-5.250 -0.3944 0.01026 0.00377 -0.0385 0.7540 0.0338
-5.000 -0.3682 0.01006 0.00354 -0.0384 0.7492 0.0361
-4.750 -0.3425 0.00977 0.00327 -0.0382 0.7443 0.0422
-4.500 -0.3171 0.00947 0.00302 -0.0381 0.7397 0.0570
-4.250 -0.2941 0.00891 0.00270 -0.0376 0.7352 0.1178
-4.000 -0.2723 0.00811 0.00234 -0.0372 0.7308 0.2223
-3.750 -0.2514 0.00717 0.00194 -0.0367 0.7261 0.3606
-3.500 -0.2291 0.00639 0.00165 -0.0363 0.7217 0.4971
-3.250 -0.2017 0.00620 0.00159 -0.0364 0.7177 0.5442
-3.000 -0.1731 0.00614 0.00155 -0.0367 0.7137 0.5661
-2.750 -0.1444 0.00610 0.00151 -0.0370 0.7097 0.5807
-2.500 -0.1159 0.00609 0.00149 -0.0372 0.7057 0.5938
-2.250 -0.0871 0.00608 0.00150 -0.0375 0.7019 0.6115
-2.000 -0.0583 0.00608 0.00152 -0.0377 0.6981 0.6279
-1.750 -0.0297 0.00609 0.00154 -0.0379 0.6944 0.6399
-1.500 -0.0006 0.00614 0.00154 -0.0382 0.6907 0.6467
-1.250 0.0282 0.00612 0.00153 -0.0385 0.6871 0.6516
-1.000 0.0575 0.00611 0.00152 -0.0389 0.6836 0.6551
-0.750 0.0867 0.00612 0.00151 -0.0393 0.6800 0.6585
-0.500 0.1159 0.00615 0.00149 -0.0397 0.6766 0.6616
-0.250 0.1447 0.00616 0.00149 -0.0400 0.6729 0.6651
0.000 0.1739 0.00614 0.00150 -0.0404 0.6698 0.6685
0.250 0.2032 0.00614 0.00151 -0.0408 0.6665 0.6719
0.500 0.2324 0.00616 0.00153 -0.0411 0.6632 0.6755
0.750 0.2614 0.00620 0.00154 -0.0415 0.6598 0.6788
1.000 0.2903 0.00621 0.00157 -0.0418 0.6565 0.6824
1.250 0.3194 0.00621 0.00161 -0.0422 0.6534 0.6860
1.500 0.3486 0.00623 0.00164 -0.0426 0.6501 0.6899
1.750 0.3776 0.00626 0.00167 -0.0429 0.6462 0.6935
2.000 0.4061 0.00629 0.00171 -0.0431 0.6410 0.6973
2.250 0.4349 0.00627 0.00174 -0.0434 0.6351 0.7012
2.500 0.4634 0.00630 0.00176 -0.0436 0.6283 0.7053
2.750 0.4919 0.00631 0.00178 -0.0439 0.6182 0.7093
3.000 0.5197 0.00632 0.00180 -0.0439 0.6050 0.7136
3.250 0.5474 0.00637 0.00184 -0.0440 0.5893 0.7178
3.500 0.5751 0.00644 0.00189 -0.0441 0.5752 0.7222
3.750 0.6029 0.00653 0.00196 -0.0442 0.5609 0.7264
4.000 0.6299 0.00661 0.00205 -0.0441 0.5410 0.7311
4.250 0.6557 0.00680 0.00216 -0.0439 0.5093 0.7360
4.500 0.6773 0.00731 0.00240 -0.0430 0.4408 0.7409
4.750 0.6912 0.00835 0.00292 -0.0410 0.3225 0.7458
5.000 0.7052 0.00936 0.00346 -0.0390 0.2183 0.7511
5.250 0.7206 0.01023 0.00395 -0.0373 0.1384 0.7566
5.500 0.7371 0.01096 0.00441 -0.0357 0.0806 0.7621
5.750 0.7556 0.01153 0.00483 -0.0343 0.0478 0.7681
6.000 0.7771 0.01192 0.00518 -0.0334 0.0375 0.7740
6.250 0.7980 0.01230 0.00555 -0.0324 0.0323 0.7797
6.500 0.8202 0.01258 0.00587 -0.0316 0.0298 0.7860
6.750 0.8396 0.01301 0.00630 -0.0304 0.0269 0.7922
7.000 0.8603 0.01331 0.00667 -0.0293 0.0256 0.7988
7.250 0.8805 0.01364 0.00703 -0.0282 0.0243 0.8060
7.500 0.8976 0.01398 0.00742 -0.0265 0.0232 0.8132
7.750 0.9103 0.01445 0.00794 -0.0241 0.0221 0.8216
8.000 0.9213 0.01503 0.00859 -0.0214 0.0213 0.8299
8.250 0.9377 0.01542 0.00903 -0.0198 0.0208 0.8386
8.500 0.9520 0.01588 0.00958 -0.0178 0.0203 0.8479
8.750 0.9666 0.01636 0.01012 -0.0160 0.0197 0.8579
9.000 0.9803 0.01690 0.01072 -0.0141 0.0192 0.8694
9.250 0.9944 0.01738 0.01127 -0.0124 0.0185 0.8818
9.500 1.0047 0.01807 0.01203 -0.0101 0.0181 0.8967
9.750 1.0099 0.01902 0.01309 -0.0072 0.0176 0.9158
10.000 1.0143 0.01997 0.01419 -0.0042 0.0172 0.9442
10.250 1.0399 0.02062 0.01493 -0.0052 0.0169 1.0000
10.500 1.0549 0.02141 0.01576 -0.0042 0.0166 1.0000
10.750 1.0692 0.02226 0.01665 -0.0032 0.0163 1.0000
11.000 1.0824 0.02320 0.01764 -0.0021 0.0161 1.0000
11.250 1.0953 0.02418 0.01866 -0.0010 0.0158 1.0000
11.500 1.1079 0.02520 0.01973 0.0001 0.0156 1.0000
11.750 1.1207 0.02622 0.02078 0.0011 0.0152 1.0000
12.000 1.1333 0.02726 0.02186 0.0020 0.0150 1.0000
12.250 1.1458 0.02832 0.02296 0.0029 0.0147 1.0000
12.500 1.1568 0.02953 0.02421 0.0039 0.0145 1.0000
12.750 1.1663 0.03091 0.02562 0.0049 0.0142 1.0000
13.000 1.1713 0.03292 0.02772 0.0063 0.0138 1.0000
13.250 1.1810 0.03445 0.02933 0.0073 0.0137 1.0000
13.500 1.1921 0.03569 0.03065 0.0079 0.0136 1.0000
13.750 1.2021 0.03709 0.03213 0.0085 0.0134 1.0000
14.000 1.2112 0.03862 0.03375 0.0092 0.0133 1.0000
14.250 1.2193 0.04028 0.03550 0.0098 0.0131 1.0000
14.500 1.2267 0.04201 0.03732 0.0103 0.0130 1.0000
14.750 1.2331 0.04392 0.03932 0.0108 0.0127 1.0000
15.000 1.2383 0.04598 0.04149 0.0113 0.0126 1.0000
15.250 1.2426 0.04818 0.04379 0.0116 0.0125 1.0000
15.500 1.2459 0.05053 0.04623 0.0117 0.0123 1.0000
15.750 1.2482 0.05307 0.04888 0.0118 0.0122 1.0000
16.000 1.2501 0.05565 0.05156 0.0116 0.0121 1.0000
16.250 1.2500 0.05861 0.05464 0.0114 0.0120 1.0000
16.500 1.2489 0.06178 0.05792 0.0109 0.0119 1.0000
16.750 1.2473 0.06511 0.06135 0.0102 0.0117 1.0000
17.000 1.2440 0.06878 0.06515 0.0092 0.0117 1.0000
17.250 1.2457 0.07183 0.06823 0.0081 0.0115 1.0000
17.500 1.2388 0.07629 0.07283 0.0067 0.0115 1.0000
17.750 1.2351 0.08041 0.07703 0.0050 0.0114 1.0000
18.000 1.2315 0.08459 0.08128 0.0032 0.0112 1.0000
18.250 1.2167 0.09084 0.08772 0.0005 0.0112 1.0000
18.500 1.2085 0.09619 0.09315 -0.0022 0.0111 1.0000
18.750 1.1936 0.10298 0.10011 -0.0058 0.0111 1.0000
19.000 1.1749 0.11080 0.10810 -0.0102 0.0111 1.0000
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