FX 71-L-150/30 AIRFOIL (fx71l150-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 71-L-150/30 AIRFOIL (fx71l150-il) Reynolds number: 50,000 Max Cl/Cd: 27.29 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx71l150-il-50000.txt Download as CSV file: xf-fx71l150-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: FX 71-L-150/30 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7301 0.09495 0.08752 -0.0225 1.0000 0.1163
-11.750 -0.7469 0.08789 0.08044 -0.0256 1.0000 0.1147
-11.500 -0.7809 0.08009 0.07256 -0.0295 1.0000 0.1126
-11.250 -0.8224 0.07319 0.06550 -0.0323 1.0000 0.1104
-11.000 -0.8623 0.06779 0.05986 -0.0329 1.0000 0.1086
-10.750 -0.8975 0.06370 0.05547 -0.0309 1.0000 0.1073
-10.500 -0.9167 0.05987 0.05128 -0.0290 1.0000 0.1066
-10.250 -0.9192 0.05633 0.04744 -0.0277 1.0000 0.1068
-10.000 -0.9102 0.05317 0.04412 -0.0268 1.0000 0.1084
-9.750 -0.9010 0.05027 0.04101 -0.0257 1.0000 0.1110
-9.500 -0.8930 0.04739 0.03779 -0.0244 1.0000 0.1140
-9.250 -0.8825 0.04450 0.03453 -0.0231 1.0000 0.1180
-9.000 -0.8576 0.04199 0.03209 -0.0230 1.0000 0.1251
-8.750 -0.8347 0.03924 0.02920 -0.0224 1.0000 0.1337
-8.500 -0.8089 0.03686 0.02685 -0.0220 1.0000 0.1475
-8.250 -0.7908 0.03503 0.02528 -0.0211 1.0000 0.1687
-8.000 -0.7804 0.03330 0.02358 -0.0194 1.0000 0.1944
-7.750 -0.7650 0.03134 0.02205 -0.0179 1.0000 0.2292
-7.500 -0.7522 0.02940 0.02071 -0.0157 1.0000 0.2735
-7.250 -0.7489 0.02785 0.01982 -0.0122 1.0000 0.3297
-7.000 -0.7490 0.02745 0.02013 -0.0072 1.0000 0.3957
-6.750 -0.7437 0.02882 0.02194 -0.0013 1.0000 0.4564
-6.500 -0.7344 0.03091 0.02410 0.0046 1.0000 0.4998
-6.250 -0.6931 0.03548 0.02861 0.0094 1.0000 0.5351
-6.000 -0.6855 0.03706 0.03009 0.0148 1.0000 0.5607
-5.750 -0.6089 0.04272 0.03548 0.0175 1.0000 0.5873
-5.500 -0.5863 0.04424 0.03685 0.0213 1.0000 0.6103
-5.250 -0.5884 0.04432 0.03686 0.0261 1.0000 0.6308
-5.000 -0.6021 0.04366 0.03618 0.0313 1.0000 0.6503
-4.750 -0.5432 0.04559 0.03786 0.0314 1.0000 0.6734
-4.500 -0.5532 0.04488 0.03709 0.0361 1.0000 0.6920
-4.250 -0.5303 0.04490 0.03699 0.0378 1.0000 0.7114
-4.000 -0.5290 0.04426 0.03628 0.0413 1.0000 0.7303
-3.750 -0.5134 0.04381 0.03573 0.0431 1.0000 0.7484
-3.500 -0.4888 0.04343 0.03523 0.0435 1.0000 0.7654
-3.250 -0.4777 0.04273 0.03442 0.0451 1.0000 0.7809
-3.000 -0.4637 0.04207 0.03367 0.0463 1.0000 0.7961
-2.750 -0.4464 0.04150 0.03301 0.0469 1.0000 0.8115
-2.500 -0.4287 0.04090 0.03232 0.0471 1.0000 0.8254
-2.250 -0.4102 0.04029 0.03162 0.0470 0.9995 0.8381
-2.000 -0.3573 0.04007 0.03124 0.0407 0.9923 0.8511
-1.750 -0.3136 0.03980 0.03086 0.0360 0.9844 0.8646
-1.500 -0.2525 0.03970 0.03063 0.0284 0.9770 0.8769
-1.250 -0.1997 0.03944 0.03029 0.0219 0.9697 0.8870
-1.000 -0.1797 0.03920 0.02999 0.0208 0.9631 0.8969
-0.750 -0.1247 0.03900 0.02974 0.0140 0.9562 0.9056
-0.500 -0.0939 0.03897 0.02966 0.0111 0.9491 0.9152
-0.250 -0.0418 0.03883 0.02951 0.0047 0.9412 0.9242
0.000 -0.0004 0.03895 0.02961 0.0001 0.9338 0.9338
0.250 0.0415 0.03882 0.02951 -0.0047 0.9243 0.9412
0.500 0.0936 0.03896 0.02966 -0.0110 0.9150 0.9492
0.750 0.1254 0.03899 0.02973 -0.0141 0.9054 0.9563
1.000 0.1797 0.03919 0.02998 -0.0208 0.8969 0.9631
1.250 0.1999 0.03943 0.03028 -0.0220 0.8871 0.9697
1.500 0.2527 0.03969 0.03063 -0.0284 0.8771 0.9770
1.750 0.3124 0.03980 0.03086 -0.0358 0.8647 0.9843
2.000 0.3575 0.04006 0.03123 -0.0407 0.8511 0.9923
2.250 0.4105 0.04027 0.03159 -0.0471 0.8382 0.9996
2.500 0.4287 0.04088 0.03230 -0.0471 0.8255 1.0000
2.750 0.4469 0.04147 0.03298 -0.0469 0.8114 1.0000
3.000 0.4638 0.04206 0.03365 -0.0463 0.7962 1.0000
3.250 0.4778 0.04271 0.03440 -0.0451 0.7809 1.0000
3.500 0.4896 0.04339 0.03518 -0.0435 0.7653 1.0000
3.750 0.5116 0.04383 0.03575 -0.0429 0.7486 1.0000
4.000 0.5292 0.04424 0.03626 -0.0413 0.7303 1.0000
4.250 0.5295 0.04491 0.03700 -0.0377 0.7116 1.0000
4.500 0.5538 0.04484 0.03707 -0.0361 0.6921 1.0000
4.750 0.5433 0.04557 0.03783 -0.0314 0.6734 1.0000
5.000 0.6006 0.04372 0.03622 -0.0312 0.6504 1.0000
5.250 0.5885 0.04429 0.03683 -0.0260 0.6308 1.0000
5.500 0.5865 0.04421 0.03683 -0.0213 0.6104 1.0000
5.750 0.6082 0.04274 0.03549 -0.0174 0.5874 1.0000
6.000 0.6837 0.03719 0.03022 -0.0148 0.5609 1.0000
6.250 0.6931 0.03547 0.02859 -0.0094 0.5352 1.0000
6.500 0.7343 0.03090 0.02409 -0.0046 0.4999 1.0000
6.750 0.7437 0.02881 0.02193 0.0013 0.4565 1.0000
7.000 0.7489 0.02744 0.02013 0.0072 0.3957 1.0000
7.250 0.7489 0.02785 0.01981 0.0122 0.3297 1.0000
7.500 0.7523 0.02940 0.02070 0.0157 0.2734 1.0000
7.750 0.7652 0.03135 0.02205 0.0179 0.2292 1.0000
8.000 0.7808 0.03329 0.02359 0.0194 0.1947 1.0000
8.250 0.7911 0.03504 0.02528 0.0211 0.1687 1.0000
8.500 0.8092 0.03687 0.02685 0.0220 0.1475 1.0000
8.750 0.8349 0.03926 0.02920 0.0224 0.1334 1.0000
9.000 0.8577 0.04200 0.03210 0.0229 0.1250 1.0000
9.250 0.8826 0.04448 0.03451 0.0231 0.1180 1.0000
9.500 0.8936 0.04740 0.03779 0.0243 0.1142 1.0000
9.750 0.9013 0.05026 0.04100 0.0257 0.1110 1.0000
10.000 0.9101 0.05318 0.04414 0.0267 0.1085 1.0000
10.250 0.9194 0.05634 0.04746 0.0276 0.1068 1.0000
10.500 0.9180 0.05989 0.05128 0.0289 0.1065 1.0000
10.750 0.8958 0.06374 0.05554 0.0309 0.1075 1.0000
11.000 0.8625 0.06781 0.05988 0.0328 0.1087 1.0000
11.250 0.8232 0.07320 0.06550 0.0322 0.1105 1.0000
11.500 0.7823 0.08007 0.07254 0.0294 0.1127 1.0000
11.750 0.7482 0.08790 0.08045 0.0256 0.1148 1.0000
12.000 0.7332 0.09470 0.08726 0.0226 0.1163 1.0000
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Polar data table (+)
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