FX 63-158 AIRFOIL (fx63158-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: FX 63-158 AIRFOIL (fx63158-il) Reynolds number: 500,000 Max Cl/Cd: 76.92 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63158-il-500000.txt Download as CSV file: xf-fx63158-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-158 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.1866 0.09893 0.09686 -0.0606 0.9902 0.0174
-10.750 -0.1867 0.09237 0.09031 -0.0648 0.9876 0.0178
-10.500 -0.3018 0.10308 0.10094 -0.0490 0.9985 0.0161
-10.250 -0.1988 0.07488 0.07284 -0.0757 0.9802 0.0180
-10.000 -0.2119 0.06618 0.06409 -0.0812 0.9756 0.0180
-9.750 -0.2283 0.05909 0.05693 -0.0859 0.9613 0.0180
-9.500 -0.2444 0.05275 0.05048 -0.0906 0.9491 0.0180
-9.250 -0.2561 0.04682 0.04440 -0.0962 0.9368 0.0180
-9.000 -0.2661 0.04080 0.03809 -0.1043 0.9202 0.0180
-8.750 -0.3000 0.05407 0.05161 -0.0973 0.9327 0.0175
-8.500 -0.3014 0.04622 0.04297 -0.1107 0.9096 0.0180
-8.250 -0.2313 0.03782 0.03417 -0.1281 0.8751 0.0185
-8.000 -0.2027 0.03523 0.03114 -0.1319 0.8056 0.0188
-7.750 -0.1923 0.03352 0.02912 -0.1309 0.7695 0.0191
-7.500 -0.1820 0.03174 0.02703 -0.1295 0.7373 0.0196
-7.250 -0.1689 0.02992 0.02488 -0.1284 0.7159 0.0204
-6.500 -0.1123 0.01242 0.00672 -0.1208 0.6550 0.0235
-6.250 -0.0911 0.01117 0.00508 -0.1206 0.6459 0.0264
-6.000 -0.0681 0.01017 0.00403 -0.1205 0.6361 0.0276
-5.750 -0.0444 0.00934 0.00297 -0.1206 0.6277 0.0314
-5.500 -0.0189 0.00874 0.00205 -0.1207 0.6195 0.0358
-5.250 0.0060 0.01676 0.00950 -0.1214 0.6200 0.0142
-5.000 0.0290 0.01574 0.00842 -0.1203 0.6131 0.0137
-4.750 0.0531 0.01493 0.00755 -0.1195 0.6061 0.0136
-4.500 0.0775 0.01431 0.00684 -0.1190 0.5987 0.0138
-4.250 0.1037 0.01379 0.00625 -0.1189 0.5898 0.0142
-4.000 0.1301 0.01336 0.00572 -0.1189 0.5790 0.0148
-3.750 0.1583 0.01270 0.00505 -0.1196 0.5678 0.0156
-3.500 0.1872 0.01234 0.00463 -0.1203 0.5594 0.0169
-3.250 0.2170 0.01200 0.00421 -0.1211 0.5522 0.0185
-3.000 0.2471 0.01166 0.00378 -0.1220 0.5455 0.0199
-2.750 0.2779 0.01142 0.00346 -0.1228 0.5397 0.0219
-2.500 0.3084 0.01122 0.00326 -0.1235 0.5331 0.0387
-2.250 0.3401 0.01091 0.00302 -0.1247 0.5272 0.0931
-2.000 0.3701 0.01081 0.00291 -0.1254 0.5203 0.1078
-1.750 0.4005 0.01067 0.00281 -0.1263 0.5128 0.1437
-1.500 0.4345 0.01027 0.00265 -0.1282 0.5045 0.2458
-1.250 0.4686 0.00989 0.00251 -0.1303 0.4946 0.3363
-1.000 0.5098 0.00917 0.00249 -0.1343 0.4846 0.5746
-0.750 0.5378 0.00934 0.00267 -0.1343 0.4769 0.6142
-0.500 0.5665 0.00943 0.00272 -0.1346 0.4695 0.6232
-0.250 0.5947 0.00957 0.00279 -0.1347 0.4619 0.6337
0.000 0.6227 0.00970 0.00291 -0.1347 0.4553 0.6429
0.250 0.6510 0.00987 0.00302 -0.1348 0.4448 0.6536
0.500 0.6778 0.01003 0.00316 -0.1346 0.4324 0.6587
0.750 0.7047 0.01021 0.00326 -0.1345 0.4210 0.6625
1.000 0.7318 0.01039 0.00335 -0.1344 0.4115 0.6664
1.250 0.7600 0.01054 0.00344 -0.1346 0.4032 0.6706
1.500 0.7866 0.01071 0.00359 -0.1344 0.3950 0.6738
1.750 0.8135 0.01085 0.00374 -0.1343 0.3856 0.6775
2.000 0.8395 0.01109 0.00390 -0.1340 0.3664 0.6813
2.250 0.8646 0.01144 0.00410 -0.1337 0.3474 0.6852
2.500 0.8910 0.01165 0.00428 -0.1335 0.3362 0.6896
2.750 0.9154 0.01190 0.00454 -0.1329 0.3233 0.6943
3.000 0.9381 0.01237 0.00488 -0.1320 0.2949 0.7000
3.250 0.9637 0.01271 0.00513 -0.1317 0.2855 0.7049
3.500 0.9888 0.01287 0.00533 -0.1313 0.2778 0.7078
3.750 1.0117 0.01326 0.00564 -0.1306 0.2477 0.7100
4.000 1.0334 0.01374 0.00599 -0.1297 0.2299 0.7126
4.250 1.0579 0.01402 0.00626 -0.1292 0.2209 0.7153
4.500 1.0823 0.01432 0.00653 -0.1289 0.1964 0.7177
4.750 1.1042 0.01481 0.00689 -0.1281 0.1817 0.7196
5.000 1.1289 0.01508 0.00715 -0.1278 0.1775 0.7215
5.250 1.1531 0.01534 0.00741 -0.1274 0.1738 0.7234
5.500 1.1768 0.01554 0.00767 -0.1268 0.1712 0.7256
5.750 1.2006 0.01574 0.00793 -0.1262 0.1686 0.7282
6.000 1.2239 0.01599 0.00823 -0.1256 0.1635 0.7311
6.250 1.2470 0.01625 0.00854 -0.1249 0.1477 0.7343
6.500 1.2647 0.01686 0.00904 -0.1235 0.1360 0.7369
6.750 1.2854 0.01727 0.00943 -0.1225 0.1321 0.7390
7.000 1.3037 0.01765 0.00983 -0.1211 0.1280 0.7410
7.250 1.3225 0.01794 0.01019 -0.1197 0.1248 0.7430
7.500 1.3411 0.01826 0.01058 -0.1183 0.1197 0.7449
7.750 1.3590 0.01864 0.01102 -0.1168 0.1148 0.7468
8.000 1.3718 0.01931 0.01163 -0.1147 0.0965 0.7485
8.250 1.3842 0.02000 0.01229 -0.1125 0.0925 0.7501
8.500 1.3970 0.02069 0.01300 -0.1105 0.0884 0.7515
8.750 1.4122 0.02126 0.01365 -0.1089 0.0850 0.7528
9.000 1.4232 0.02207 0.01451 -0.1068 0.0813 0.7540
9.250 1.4390 0.02264 0.01515 -0.1054 0.0780 0.7552
9.500 1.4517 0.02341 0.01591 -0.1037 0.0643 0.7562
9.750 1.4582 0.02453 0.01699 -0.1014 0.0618 0.7576
10.000 1.4649 0.02570 0.01820 -0.0993 0.0595 0.7589
10.250 1.4717 0.02695 0.01952 -0.0974 0.0576 0.7602
10.500 1.4772 0.02837 0.02106 -0.0955 0.0562 0.7617
10.750 1.4793 0.03016 0.02297 -0.0937 0.0545 0.7633
11.000 1.4775 0.03242 0.02532 -0.0918 0.0528 0.7650
11.250 1.4734 0.03509 0.02808 -0.0902 0.0510 0.7669
11.500 1.4889 0.03610 0.02920 -0.0899 0.0491 0.7687
11.750 1.4988 0.03769 0.03089 -0.0894 0.0463 0.7703
12.000 1.5053 0.03967 0.03293 -0.0888 0.0436 0.7717
12.250 1.5216 0.04072 0.03408 -0.0887 0.0390 0.7732
12.500 1.5288 0.04269 0.03606 -0.0884 0.0347 0.7747
12.750 1.5319 0.04514 0.03850 -0.0880 0.0318 0.7763
13.000 1.5344 0.04772 0.04115 -0.0877 0.0297 0.7778
13.250 1.5362 0.05044 0.04397 -0.0875 0.0282 0.7794
13.500 1.5366 0.05340 0.04701 -0.0874 0.0267 0.7810
13.750 1.5362 0.05653 0.05023 -0.0873 0.0253 0.7827
14.000 1.5353 0.05981 0.05359 -0.0874 0.0239 0.7844
14.250 1.5393 0.06256 0.05644 -0.0877 0.0231 0.7863
14.500 1.5432 0.06537 0.05934 -0.0880 0.0215 0.7883
14.750 1.5446 0.06859 0.06264 -0.0884 0.0194 0.7902
15.000 1.5447 0.07203 0.06614 -0.0889 0.0174 0.7921
15.250 1.5450 0.07548 0.06966 -0.0895 0.0154 0.7941
15.500 1.5433 0.07931 0.07354 -0.0902 0.0135 0.7959
15.750 1.5431 0.08300 0.07732 -0.0911 0.0120 0.7979
16.000 1.5414 0.08697 0.08136 -0.0920 0.0104 0.7999
16.250 1.5413 0.09080 0.08529 -0.0930 0.0092 0.8020
16.500 1.5390 0.09498 0.08955 -0.0942 0.0067 0.8041
16.750 1.5340 0.09968 0.09431 -0.0956 0.0049 0.8061
17.000 1.5306 0.10421 0.09892 -0.0971 0.0046 0.8081
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