NACA 67 (naca671215-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 67 (naca671215-il) Reynolds number: 200,000 Max Cl/Cd: 33.39 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca671215-il-200000-n5.txt Download as CSV file: xf-naca671215-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 67
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6392 0.06077 0.05605 -0.1148 0.9669 0.0216
-13.750 -0.6580 0.05539 0.05039 -0.1171 0.9642 0.0216
-13.500 -0.6729 0.05116 0.04589 -0.1177 0.9607 0.0217
-13.250 -0.6815 0.04812 0.04263 -0.1172 0.9566 0.0219
-13.000 -0.6871 0.04526 0.03952 -0.1165 0.9532 0.0221
-12.750 -0.6889 0.04261 0.03660 -0.1157 0.9504 0.0224
-12.500 -0.6932 0.04038 0.03411 -0.1134 0.9460 0.0225
-12.250 -0.6928 0.03845 0.03194 -0.1114 0.9421 0.0228
-12.000 -0.6888 0.03655 0.02978 -0.1096 0.9390 0.0232
-11.750 -0.6811 0.03471 0.02766 -0.1081 0.9365 0.0237
-11.500 -0.6750 0.03319 0.02590 -0.1057 0.9327 0.0241
-11.250 -0.6646 0.03175 0.02419 -0.1039 0.9295 0.0246
-11.000 -0.6514 0.03046 0.02260 -0.1023 0.9270 0.0253
-10.750 -0.6344 0.02945 0.02155 -0.1015 0.9250 0.0260
-10.500 -0.6175 0.02869 0.02072 -0.1006 0.9231 0.0267
-10.250 -0.5985 0.02785 0.01978 -0.0999 0.9216 0.0276
-10.000 -0.5809 0.02704 0.01885 -0.0988 0.9195 0.0285
-9.750 -0.5618 0.02621 0.01787 -0.0978 0.9174 0.0296
-9.500 -0.5413 0.02544 0.01695 -0.0971 0.9155 0.0306
-9.250 -0.5221 0.02467 0.01617 -0.0962 0.9136 0.0317
-9.000 -0.5035 0.02409 0.01557 -0.0952 0.9116 0.0328
-8.750 -0.4838 0.02353 0.01495 -0.0944 0.9098 0.0343
-8.500 -0.4630 0.02301 0.01433 -0.0936 0.9082 0.0365
-8.250 -0.4431 0.02242 0.01369 -0.0928 0.9070 0.0382
-8.000 -0.4233 0.02198 0.01325 -0.0920 0.9058 0.0406
-7.750 -0.4088 0.02173 0.01295 -0.0900 0.9035 0.0428
-7.500 -0.3939 0.02149 0.01264 -0.0881 0.9012 0.0449
-7.250 -0.3806 0.02111 0.01229 -0.0860 0.8989 0.0476
-7.000 -0.3650 0.02082 0.01198 -0.0843 0.8968 0.0505
-6.750 -0.3479 0.02051 0.01161 -0.0827 0.8949 0.0533
-6.500 -0.3317 0.02011 0.01119 -0.0810 0.8932 0.0560
-6.250 -0.3147 0.01976 0.01085 -0.0795 0.8918 0.0601
-6.000 -0.2962 0.01948 0.01050 -0.0781 0.8907 0.0642
-5.750 -0.2855 0.01929 0.01034 -0.0753 0.8886 0.0690
-5.500 -0.2872 0.01946 0.01052 -0.0700 0.8845 0.0733
-5.250 -0.2805 0.01937 0.01045 -0.0662 0.8813 0.0805
-5.000 -0.2715 0.01920 0.01034 -0.0630 0.8790 0.0943
-4.750 -0.2613 0.01895 0.01019 -0.0599 0.8772 0.1184
-4.500 -0.2516 0.01859 0.01002 -0.0568 0.8756 0.1582
-4.250 -0.2411 0.01810 0.00979 -0.0539 0.8742 0.2180
-4.000 -0.2778 0.01889 0.01056 -0.0413 0.8657 0.2168
-3.750 -0.2762 0.01837 0.01037 -0.0366 0.8628 0.2925
-3.500 -0.2765 0.01761 0.01009 -0.0316 0.8606 0.3975
-3.250 -0.2782 0.01663 0.00978 -0.0260 0.8588 0.5394
-2.750 -0.2750 0.01791 0.01203 -0.0138 0.8495 0.7472
-2.500 -0.2610 0.01799 0.01204 -0.0110 0.8471 0.7744
-2.250 -0.2438 0.01819 0.01217 -0.0087 0.8455 0.7981
-2.000 -0.2090 0.01945 0.01345 -0.0084 0.8448 0.8218
-1.750 -0.1672 0.02106 0.01505 -0.0092 0.8445 0.8430
-1.500 -0.1243 0.02172 0.01566 -0.0116 0.8442 0.8489
-1.250 -0.0901 0.02183 0.01570 -0.0130 0.8436 0.8510
-1.000 -0.1372 0.02188 0.01576 0.0013 0.8329 0.8624
-0.750 -0.1077 0.02191 0.01574 0.0007 0.8314 0.8636
-0.500 -0.0767 0.02189 0.01567 -0.0001 0.8302 0.8649
-0.250 -0.0460 0.02185 0.01560 -0.0009 0.8291 0.8663
0.000 -0.0155 0.02179 0.01551 -0.0017 0.8281 0.8678
0.500 -0.0208 0.02158 0.01525 0.0093 0.8157 0.8781
0.750 0.0103 0.02152 0.01517 0.0084 0.8142 0.8790
1.000 0.0422 0.02141 0.01505 0.0074 0.8130 0.8798
1.250 0.0749 0.02128 0.01492 0.0062 0.8119 0.8805
1.750 0.0974 0.02141 0.01507 0.0119 0.7997 0.8852
2.000 0.1281 0.02121 0.01488 0.0112 0.7979 0.8863
2.250 0.1609 0.02097 0.01466 0.0101 0.7965 0.8874
2.750 0.1872 0.02071 0.01444 0.0150 0.7834 0.8928
3.000 0.2205 0.02036 0.01412 0.0139 0.7816 0.8937
3.500 0.2620 0.02001 0.01386 0.0164 0.7681 0.8964
3.750 0.2962 0.01949 0.01339 0.0155 0.7639 0.8972
4.000 0.3112 0.01933 0.01328 0.0178 0.7534 0.8990
4.500 0.3466 0.01869 0.01275 0.0217 0.7286 0.9025
5.000 0.3855 0.01781 0.01195 0.0252 0.6883 0.9062
5.250 0.4932 0.01477 0.00834 0.0139 0.5691 0.9016
5.500 0.4988 0.01528 0.00832 0.0180 0.4751 0.9040
5.750 0.4957 0.01597 0.00865 0.0231 0.4043 0.9078
6.000 0.4960 0.01670 0.00905 0.0274 0.3374 0.9106
6.250 0.5006 0.01744 0.00949 0.0310 0.2749 0.9126
6.500 0.5086 0.01813 0.00993 0.0337 0.2189 0.9147
6.750 0.5186 0.01883 0.01037 0.0361 0.1661 0.9168
7.000 0.5312 0.01948 0.01081 0.0380 0.1252 0.9190
7.250 0.5456 0.02005 0.01125 0.0396 0.0980 0.9213
7.500 0.5612 0.02058 0.01170 0.0411 0.0810 0.9239
7.750 0.5774 0.02109 0.01218 0.0425 0.0704 0.9260
8.000 0.5936 0.02164 0.01271 0.0438 0.0635 0.9278
8.250 0.6112 0.02212 0.01324 0.0449 0.0587 0.9299
8.500 0.6272 0.02270 0.01384 0.0462 0.0549 0.9322
8.750 0.6435 0.02328 0.01445 0.0475 0.0513 0.9346
9.000 0.6607 0.02380 0.01503 0.0485 0.0476 0.9371
9.250 0.6757 0.02452 0.01572 0.0497 0.0442 0.9396
9.500 0.6953 0.02504 0.01633 0.0503 0.0413 0.9416
9.750 0.7132 0.02567 0.01703 0.0511 0.0389 0.9441
10.000 0.7288 0.02644 0.01782 0.0521 0.0370 0.9470
10.250 0.7459 0.02711 0.01857 0.0530 0.0346 0.9504
10.500 0.7642 0.02782 0.01936 0.0536 0.0326 0.9533
10.750 0.7822 0.02863 0.02021 0.0539 0.0307 0.9561
11.000 0.7997 0.02956 0.02121 0.0544 0.0293 0.9591
11.250 0.8179 0.03048 0.02224 0.0549 0.0279 0.9622
11.500 0.8369 0.03145 0.02331 0.0550 0.0264 0.9650
11.750 0.8564 0.03250 0.02443 0.0548 0.0255 0.9676
12.000 0.8743 0.03377 0.02572 0.0548 0.0245 0.9706
12.250 0.8944 0.03499 0.02711 0.0546 0.0239 0.9737
12.500 0.9142 0.03639 0.02870 0.0544 0.0230 0.9766
12.750 0.9328 0.03784 0.03031 0.0541 0.0223 0.9802
13.250 0.9634 0.04071 0.03345 0.0538 0.0210 0.9990
13.500 0.9713 0.04205 0.03485 0.0550 0.0206 1.0000
13.750 0.9785 0.04362 0.03649 0.0561 0.0202 1.0000
14.000 0.9838 0.04547 0.03849 0.0573 0.0199 1.0000
14.250 0.9868 0.04762 0.04088 0.0585 0.0197 1.0000
14.500 0.9853 0.05021 0.04375 0.0598 0.0192 1.0000
14.750 0.9833 0.05285 0.04662 0.0608 0.0191 1.0000
15.000 0.9769 0.05599 0.05001 0.0618 0.0188 1.0000
15.250 0.9688 0.05941 0.05367 0.0624 0.0187 1.0000
15.500 0.9570 0.06333 0.05782 0.0626 0.0184 1.0000
15.750 0.9416 0.06799 0.06273 0.0622 0.0184 1.0000
16.000 0.9242 0.07320 0.06817 0.0611 0.0183 1.0000
16.250 0.9030 0.07940 0.07461 0.0589 0.0184 1.0000
16.500 0.8749 0.08740 0.08286 0.0553 0.0184 1.0000
16.750 0.8395 0.09780 0.09354 0.0494 0.0185 1.0000
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Polar data table (+)
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