FX 71-L-150/20 AIRFOIL (fx711520-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 71-L-150/20 AIRFOIL (fx711520-il) Reynolds number: 100,000 Max Cl/Cd: 33.27 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx711520-il-100000-n5.txt Download as CSV file: xf-fx711520-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 71-L-150/20 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.8419 0.10637 0.10038 -0.0050 1.0000 0.0276
-14.750 -0.9005 0.09106 0.08459 -0.0151 1.0000 0.0271
-14.500 -0.9268 0.08324 0.07646 -0.0196 1.0000 0.0270
-14.250 -0.9431 0.07755 0.07054 -0.0223 1.0000 0.0270
-14.000 -0.9569 0.07247 0.06520 -0.0244 1.0000 0.0269
-13.750 -0.9639 0.06839 0.06094 -0.0258 1.0000 0.0269
-13.500 -0.9682 0.06475 0.05711 -0.0267 1.0000 0.0270
-13.250 -0.9691 0.06153 0.05373 -0.0273 1.0000 0.0271
-13.000 -0.9676 0.05863 0.05069 -0.0276 1.0000 0.0272
-12.750 -0.9641 0.05595 0.04786 -0.0278 1.0000 0.0274
-12.500 -0.9587 0.05349 0.04528 -0.0278 1.0000 0.0276
-12.250 -0.9517 0.05120 0.04287 -0.0277 1.0000 0.0279
-12.000 -0.9427 0.04908 0.04063 -0.0274 1.0000 0.0282
-11.750 -0.9325 0.04711 0.03855 -0.0271 1.0000 0.0285
-11.500 -0.9209 0.04529 0.03662 -0.0267 1.0000 0.0288
-11.250 -0.9084 0.04359 0.03481 -0.0263 1.0000 0.0292
-11.000 -0.8952 0.04192 0.03304 -0.0257 1.0000 0.0298
-10.750 -0.8820 0.04039 0.03142 -0.0252 1.0000 0.0302
-10.500 -0.8708 0.03882 0.02988 -0.0248 1.0000 0.0308
-10.250 -0.8595 0.03731 0.02835 -0.0243 1.0000 0.0315
-10.000 -0.8479 0.03585 0.02686 -0.0239 1.0000 0.0325
-9.750 -0.8358 0.03444 0.02537 -0.0233 1.0000 0.0339
-9.500 -0.8251 0.03302 0.02400 -0.0230 1.0000 0.0349
-9.250 -0.8137 0.03166 0.02262 -0.0225 1.0000 0.0364
-9.000 -0.8020 0.03037 0.02130 -0.0222 0.9254 0.0383
-8.750 -0.7795 0.02905 0.01981 -0.0237 0.8870 0.0409
-8.500 -0.7666 0.02797 0.01861 -0.0229 0.8687 0.0436
-8.250 -0.7558 0.02703 0.01754 -0.0214 0.8562 0.0475
-8.000 -0.7437 0.02605 0.01650 -0.0200 0.8461 0.0532
-7.750 -0.7302 0.02513 0.01556 -0.0187 0.8381 0.0608
-7.500 -0.7151 0.02425 0.01472 -0.0177 0.8306 0.0726
-7.250 -0.6995 0.02343 0.01393 -0.0166 0.8243 0.0900
-7.000 -0.6837 0.02255 0.01319 -0.0156 0.8181 0.1139
-6.750 -0.6670 0.02172 0.01249 -0.0146 0.8117 0.1413
-6.500 -0.6508 0.02088 0.01181 -0.0135 0.8061 0.1795
-6.250 -0.6356 0.01989 0.01113 -0.0125 0.8002 0.2333
-6.000 -0.6217 0.01883 0.01055 -0.0112 0.7944 0.3064
-5.750 -0.6052 0.01819 0.01034 -0.0097 0.7896 0.3864
-5.500 -0.5838 0.01805 0.01046 -0.0085 0.7851 0.4466
-5.250 -0.5597 0.01810 0.01060 -0.0076 0.7795 0.4895
-5.000 -0.5345 0.01835 0.01084 -0.0067 0.7743 0.5186
-4.750 -0.5090 0.01856 0.01097 -0.0059 0.7699 0.5399
-4.500 -0.4823 0.01880 0.01115 -0.0053 0.7654 0.5557
-4.250 -0.4555 0.01898 0.01124 -0.0049 0.7601 0.5699
-4.000 -0.4297 0.01906 0.01118 -0.0045 0.7553 0.5840
-3.750 -0.4022 0.01940 0.01150 -0.0037 0.7515 0.5930
-3.500 -0.3771 0.01942 0.01135 -0.0032 0.7482 0.6053
-3.250 -0.3487 0.01967 0.01163 -0.0028 0.7433 0.6117
-3.000 -0.3220 0.01971 0.01160 -0.0025 0.7384 0.6200
-2.750 -0.2958 0.01971 0.01151 -0.0022 0.7341 0.6279
-2.500 -0.2687 0.01983 0.01158 -0.0016 0.7306 0.6333
-2.250 -0.2421 0.01984 0.01150 -0.0013 0.7272 0.6402
-2.000 -0.2154 0.01976 0.01137 -0.0015 0.7219 0.6474
-1.750 -0.1882 0.01981 0.01141 -0.0011 0.7168 0.6514
-1.500 -0.1614 0.01979 0.01135 -0.0008 0.7124 0.6560
-1.250 -0.1350 0.01972 0.01119 -0.0004 0.7089 0.6624
-1.000 -0.1081 0.01969 0.01114 -0.0006 0.7037 0.6685
-0.750 -0.0810 0.01976 0.01124 -0.0003 0.6985 0.6724
-0.500 -0.0541 0.01976 0.01123 0.0000 0.6940 0.6769
-0.250 -0.0271 0.01971 0.01113 0.0001 0.6905 0.6818
0.000 0.0000 0.01962 0.01096 0.0000 0.6873 0.6873
0.250 0.0271 0.01971 0.01113 -0.0001 0.6818 0.6905
0.500 0.0541 0.01976 0.01123 0.0000 0.6769 0.6941
0.750 0.0810 0.01976 0.01124 0.0003 0.6725 0.6985
1.000 0.1081 0.01969 0.01114 0.0006 0.6685 0.7037
1.250 0.1350 0.01972 0.01119 0.0004 0.6624 0.7089
1.500 0.1614 0.01979 0.01135 0.0008 0.6560 0.7124
1.750 0.1882 0.01981 0.01141 0.0011 0.6514 0.7168
2.000 0.2154 0.01976 0.01137 0.0015 0.6474 0.7219
2.250 0.2421 0.01984 0.01150 0.0013 0.6402 0.7272
2.500 0.2687 0.01983 0.01158 0.0016 0.6333 0.7306
2.750 0.2958 0.01971 0.01150 0.0022 0.6279 0.7341
3.000 0.3220 0.01971 0.01160 0.0025 0.6201 0.7384
3.250 0.3487 0.01967 0.01163 0.0028 0.6117 0.7433
3.500 0.3771 0.01942 0.01136 0.0032 0.6053 0.7482
3.750 0.4022 0.01940 0.01150 0.0037 0.5930 0.7515
4.000 0.4298 0.01906 0.01118 0.0045 0.5840 0.7553
4.250 0.4555 0.01897 0.01124 0.0049 0.5699 0.7601
4.500 0.4823 0.01880 0.01115 0.0053 0.5557 0.7654
4.750 0.5090 0.01856 0.01097 0.0059 0.5399 0.7699
5.000 0.5345 0.01835 0.01084 0.0067 0.5185 0.7744
5.250 0.5597 0.01811 0.01061 0.0076 0.4897 0.7795
5.500 0.5838 0.01805 0.01046 0.0085 0.4467 0.7851
5.750 0.6052 0.01819 0.01034 0.0097 0.3863 0.7896
6.000 0.6217 0.01883 0.01054 0.0112 0.3062 0.7944
6.250 0.6355 0.01990 0.01114 0.0125 0.2328 0.8002
6.500 0.6508 0.02088 0.01182 0.0135 0.1791 0.8060
6.750 0.6671 0.02171 0.01248 0.0146 0.1414 0.8117
7.000 0.6837 0.02255 0.01319 0.0156 0.1137 0.8181
7.250 0.6996 0.02343 0.01393 0.0165 0.0899 0.8243
7.500 0.7151 0.02426 0.01472 0.0177 0.0721 0.8307
7.750 0.7301 0.02514 0.01557 0.0187 0.0604 0.8382
8.000 0.7438 0.02605 0.01650 0.0200 0.0532 0.8461
8.250 0.7561 0.02702 0.01753 0.0213 0.0476 0.8562
8.500 0.7667 0.02798 0.01862 0.0228 0.0434 0.8688
8.750 0.7797 0.02906 0.01982 0.0236 0.0409 0.8871
9.000 0.8023 0.03038 0.02130 0.0221 0.0382 0.9255
9.250 0.8139 0.03167 0.02263 0.0225 0.0365 1.0000
9.500 0.8255 0.03302 0.02399 0.0229 0.0348 1.0000
9.750 0.8362 0.03444 0.02537 0.0233 0.0339 1.0000
10.000 0.8483 0.03586 0.02687 0.0238 0.0323 1.0000
10.250 0.8602 0.03730 0.02835 0.0243 0.0316 1.0000
10.500 0.8714 0.03882 0.02987 0.0247 0.0308 1.0000
10.750 0.8830 0.04036 0.03140 0.0251 0.0303 1.0000
11.000 0.8960 0.04191 0.03302 0.0257 0.0298 1.0000
11.250 0.9091 0.04356 0.03479 0.0262 0.0293 1.0000
11.500 0.9217 0.04527 0.03659 0.0266 0.0289 1.0000
11.750 0.9333 0.04711 0.03854 0.0270 0.0285 1.0000
12.000 0.9437 0.04908 0.04062 0.0274 0.0282 1.0000
12.250 0.9524 0.05121 0.04288 0.0276 0.0278 1.0000
12.500 0.9597 0.05348 0.04527 0.0277 0.0276 1.0000
12.750 0.9651 0.05595 0.04787 0.0277 0.0274 1.0000
13.000 0.9686 0.05863 0.05069 0.0275 0.0273 1.0000
13.250 0.9699 0.06156 0.05377 0.0272 0.0271 1.0000
13.500 0.9684 0.06484 0.05722 0.0265 0.0270 1.0000
13.750 0.9650 0.06838 0.06093 0.0256 0.0269 1.0000
14.000 0.9572 0.07255 0.06530 0.0243 0.0269 1.0000
14.250 0.9464 0.07726 0.07020 0.0224 0.0269 1.0000
14.500 0.9272 0.08335 0.07658 0.0194 0.0270 1.0000
14.750 0.9003 0.09127 0.08481 0.0148 0.0272 1.0000
15.000 0.8415 0.10671 0.10073 0.0046 0.0276 1.0000
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