NACA 65(2)-215 (naca652215-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(2)-215 (naca652215-il) Reynolds number: 200,000 Max Cl/Cd: 55.88 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca652215-il-200000-n5.txt Download as CSV file: xf-naca652215-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.6686 0.08279 0.07875 -0.0544 1.0000 0.0213
-13.500 -0.7113 0.07234 0.06806 -0.0608 1.0000 0.0211
-13.250 -0.7416 0.06536 0.06087 -0.0641 1.0000 0.0210
-13.000 -0.7655 0.05993 0.05523 -0.0658 1.0000 0.0210
-12.750 -0.7846 0.05552 0.05061 -0.0664 1.0000 0.0211
-12.500 -0.8006 0.05169 0.04656 -0.0663 1.0000 0.0212
-12.250 -0.8135 0.04837 0.04302 -0.0655 1.0000 0.0213
-12.000 -0.8233 0.04548 0.03989 -0.0642 1.0000 0.0215
-11.750 -0.8303 0.04295 0.03713 -0.0625 1.0000 0.0219
-11.500 -0.8347 0.04072 0.03467 -0.0605 1.0000 0.0222
-11.250 -0.8381 0.03878 0.03250 -0.0581 1.0000 0.0226
-11.000 -0.8415 0.03710 0.03059 -0.0550 1.0000 0.0230
-10.750 -0.8362 0.03537 0.02852 -0.0535 0.9872 0.0235
-10.500 -0.8116 0.03309 0.02604 -0.0550 0.9752 0.0239
-10.250 -0.7841 0.03133 0.02416 -0.0566 0.9654 0.0245
-10.000 -0.7565 0.02985 0.02254 -0.0580 0.9558 0.0250
-9.750 -0.7286 0.02847 0.02101 -0.0592 0.9467 0.0256
-9.500 -0.7033 0.02731 0.01970 -0.0597 0.9361 0.0264
-9.250 -0.6792 0.02626 0.01850 -0.0598 0.9257 0.0274
-9.000 -0.6549 0.02528 0.01735 -0.0598 0.9165 0.0283
-8.750 -0.6323 0.02439 0.01632 -0.0594 0.9064 0.0289
-8.500 -0.6089 0.02334 0.01519 -0.0591 0.8979 0.0296
-8.250 -0.5894 0.02241 0.01424 -0.0582 0.8887 0.0303
-8.000 -0.5718 0.02169 0.01347 -0.0570 0.8798 0.0312
-7.750 -0.5543 0.02102 0.01275 -0.0556 0.8713 0.0320
-7.500 -0.5368 0.02041 0.01208 -0.0543 0.8627 0.0333
-7.250 -0.5189 0.01985 0.01142 -0.0530 0.8553 0.0346
-7.000 -0.5006 0.01931 0.01078 -0.0517 0.8478 0.0359
-6.750 -0.4852 0.01858 0.01003 -0.0501 0.8406 0.0373
-6.500 -0.4675 0.01801 0.00940 -0.0488 0.8339 0.0389
-6.250 -0.4485 0.01751 0.00885 -0.0477 0.8268 0.0409
-6.000 -0.4284 0.01706 0.00828 -0.0466 0.8213 0.0431
-5.750 -0.4086 0.01655 0.00776 -0.0456 0.8146 0.0471
-5.500 -0.3874 0.01613 0.00729 -0.0448 0.8089 0.0522
-5.250 -0.3664 0.01566 0.00679 -0.0439 0.8041 0.0605
-5.000 -0.3455 0.01516 0.00636 -0.0431 0.7978 0.0784
-4.750 -0.3276 0.01438 0.00586 -0.0420 0.7923 0.1349
-4.500 -0.3128 0.01330 0.00528 -0.0407 0.7873 0.2481
-4.250 -0.3007 0.01202 0.00476 -0.0389 0.7813 0.4105
-4.000 -0.2806 0.01159 0.00478 -0.0376 0.7766 0.5255
-3.750 -0.2548 0.01154 0.00475 -0.0372 0.7729 0.5667
-3.500 -0.2292 0.01159 0.00485 -0.0367 0.7678 0.6037
-3.250 -0.2042 0.01183 0.00518 -0.0357 0.7629 0.6422
-3.000 -0.1778 0.01202 0.00532 -0.0352 0.7588 0.6625
-2.750 -0.1501 0.01205 0.00529 -0.0350 0.7550 0.6699
-2.500 -0.1224 0.01204 0.00523 -0.0351 0.7504 0.6752
-2.250 -0.0945 0.01199 0.00508 -0.0354 0.7462 0.6802
-2.000 -0.0663 0.01196 0.00497 -0.0355 0.7425 0.6835
-1.750 -0.0382 0.01194 0.00490 -0.0356 0.7387 0.6868
-1.500 -0.0103 0.01193 0.00486 -0.0358 0.7342 0.6908
-1.250 0.0178 0.01190 0.00477 -0.0360 0.7303 0.6949
-1.000 0.0461 0.01188 0.00469 -0.0362 0.7269 0.6987
-0.750 0.0743 0.01188 0.00467 -0.0364 0.7236 0.7019
-0.500 0.1020 0.01189 0.00469 -0.0365 0.7191 0.7055
-0.250 0.1301 0.01189 0.00467 -0.0368 0.7152 0.7095
0.000 0.1586 0.01190 0.00463 -0.0371 0.7119 0.7139
0.250 0.1869 0.01191 0.00463 -0.0372 0.7090 0.7170
0.500 0.2144 0.01195 0.00471 -0.0373 0.7048 0.7205
0.750 0.2423 0.01198 0.00476 -0.0375 0.7009 0.7245
1.000 0.2706 0.01201 0.00478 -0.0378 0.6974 0.7292
1.250 0.2987 0.01204 0.00483 -0.0379 0.6944 0.7326
1.500 0.3265 0.01209 0.00492 -0.0380 0.6909 0.7363
1.750 0.3540 0.01215 0.00505 -0.0381 0.6869 0.7405
2.000 0.3820 0.01221 0.00513 -0.0384 0.6832 0.7453
2.250 0.4099 0.01225 0.00523 -0.0384 0.6798 0.7491
2.500 0.4382 0.01231 0.00533 -0.0386 0.6770 0.7532
2.750 0.4650 0.01241 0.00553 -0.0386 0.6726 0.7579
3.000 0.4926 0.01249 0.00567 -0.0388 0.6683 0.7628
3.250 0.5201 0.01252 0.00579 -0.0387 0.6638 0.7666
3.500 0.5471 0.01257 0.00591 -0.0386 0.6581 0.7713
3.750 0.5738 0.01259 0.00602 -0.0385 0.6504 0.7769
4.000 0.6002 0.01256 0.00605 -0.0381 0.6409 0.7815
4.250 0.6246 0.01243 0.00596 -0.0372 0.6219 0.7862
4.500 0.6476 0.01228 0.00576 -0.0360 0.5903 0.7918
4.750 0.6702 0.01229 0.00573 -0.0349 0.5567 0.7972
5.000 0.6924 0.01239 0.00582 -0.0338 0.5233 0.8026
5.250 0.7103 0.01272 0.00590 -0.0320 0.4564 0.8093
5.500 0.7144 0.01373 0.00635 -0.0281 0.3459 0.8157
5.750 0.7174 0.01493 0.00707 -0.0244 0.2510 0.8231
6.000 0.7214 0.01606 0.00781 -0.0210 0.1717 0.8305
6.250 0.7270 0.01705 0.00851 -0.0178 0.1126 0.8387
6.500 0.7336 0.01784 0.00914 -0.0147 0.0784 0.8473
6.750 0.7419 0.01852 0.00976 -0.0118 0.0605 0.8569
7.000 0.7520 0.01917 0.01043 -0.0092 0.0509 0.8663
7.250 0.7637 0.01982 0.01111 -0.0070 0.0454 0.8768
7.500 0.7746 0.02050 0.01185 -0.0047 0.0416 0.8887
7.750 0.7849 0.02123 0.01264 -0.0024 0.0392 0.9025
8.000 0.7969 0.02190 0.01343 -0.0005 0.0368 0.9191
8.250 0.8109 0.02264 0.01425 0.0009 0.0348 0.9394
8.500 0.8292 0.02373 0.01538 0.0007 0.0326 0.9697
8.750 0.8445 0.02464 0.01636 0.0013 0.0312 1.0000
9.000 0.8587 0.02567 0.01743 0.0022 0.0301 1.0000
9.250 0.8728 0.02671 0.01853 0.0030 0.0292 1.0000
9.500 0.8867 0.02780 0.01964 0.0039 0.0282 1.0000
9.750 0.9005 0.02892 0.02078 0.0047 0.0275 1.0000
10.000 0.9137 0.03015 0.02200 0.0056 0.0266 1.0000
10.250 0.9280 0.03142 0.02330 0.0064 0.0259 1.0000
10.500 0.9444 0.03249 0.02447 0.0071 0.0251 1.0000
10.750 0.9607 0.03360 0.02567 0.0077 0.0245 1.0000
11.000 0.9768 0.03479 0.02694 0.0084 0.0237 1.0000
11.250 0.9930 0.03602 0.02825 0.0090 0.0231 1.0000
11.500 1.0091 0.03732 0.02963 0.0096 0.0226 1.0000
11.750 1.0247 0.03866 0.03105 0.0101 0.0222 1.0000
12.000 1.0397 0.04008 0.03254 0.0107 0.0218 1.0000
12.250 1.0546 0.04161 0.03413 0.0112 0.0215 1.0000
12.500 1.0704 0.04336 0.03595 0.0116 0.0211 1.0000
12.750 1.0819 0.04536 0.03813 0.0123 0.0208 1.0000
13.000 1.0889 0.04747 0.04049 0.0131 0.0206 1.0000
13.250 1.0922 0.04983 0.04310 0.0138 0.0202 1.0000
13.500 1.0943 0.05238 0.04589 0.0145 0.0199 1.0000
13.750 1.0931 0.05520 0.04895 0.0150 0.0195 1.0000
14.000 1.0904 0.05822 0.05219 0.0154 0.0192 1.0000
14.250 1.0851 0.06163 0.05583 0.0155 0.0190 1.0000
14.500 1.0769 0.06546 0.05989 0.0153 0.0188 1.0000
14.750 1.0659 0.06971 0.06438 0.0148 0.0187 1.0000
15.000 1.0532 0.07435 0.06924 0.0137 0.0186 1.0000
15.250 1.0374 0.07972 0.07484 0.0121 0.0185 1.0000
15.500 1.0180 0.08599 0.08134 0.0096 0.0185 1.0000
15.750 0.9954 0.09327 0.08887 0.0062 0.0185 1.0000
16.000 0.9645 0.10284 0.09871 0.0010 0.0186 1.0000
16.250 0.9270 0.11513 0.11125 -0.0067 0.0188 1.0000
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