FX 71-L-150/30 AIRFOIL (fx711530-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: FX 71-L-150/30 AIRFOIL (fx711530-il) Reynolds number: 200,000 Max Cl/Cd: 40.11 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx711530-il-200000-n5.txt Download as CSV file: xf-fx711530-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.8325 0.14632 0.14204 0.0160 1.0000 0.0183
-17.250 -0.8957 0.12530 0.12070 0.0032 1.0000 0.0179
-17.000 -0.9279 0.11346 0.10861 -0.0043 1.0000 0.0178
-16.750 -0.9517 0.10419 0.09912 -0.0100 1.0000 0.0177
-16.500 -0.9689 0.09675 0.09148 -0.0143 1.0000 0.0176
-16.250 -0.9831 0.09020 0.08473 -0.0180 1.0000 0.0176
-16.000 -0.9945 0.08444 0.07879 -0.0210 1.0000 0.0176
-15.750 -1.0049 0.07908 0.07324 -0.0235 1.0000 0.0176
-15.500 -1.0112 0.07456 0.06855 -0.0255 1.0000 0.0176
-15.250 -1.0158 0.07047 0.06430 -0.0271 1.0000 0.0176
-15.000 -1.0198 0.06661 0.06027 -0.0284 1.0000 0.0178
-14.750 -1.0205 0.06333 0.05685 -0.0293 1.0000 0.0177
-14.500 -1.0202 0.06030 0.05369 -0.0300 1.0000 0.0178
-14.250 -1.0195 0.05739 0.05065 -0.0305 1.0000 0.0179
-14.000 -1.0171 0.05477 0.04789 -0.0308 1.0000 0.0180
-13.750 -1.0131 0.05239 0.04541 -0.0310 1.0000 0.0180
-13.500 -1.0085 0.05011 0.04303 -0.0310 1.0000 0.0181
-13.250 -1.0037 0.04788 0.04066 -0.0309 1.0000 0.0184
-13.000 -0.9978 0.04585 0.03857 -0.0307 1.0000 0.0185
-12.750 -0.9913 0.04394 0.03659 -0.0305 1.0000 0.0185
-12.500 -0.9850 0.04205 0.03465 -0.0302 1.0000 0.0186
-12.250 -0.9781 0.04025 0.03280 -0.0299 1.0000 0.0188
-12.000 -0.9709 0.03853 0.03103 -0.0295 1.0000 0.0190
-11.750 -0.9630 0.03688 0.02933 -0.0290 1.0000 0.0191
-11.500 -0.9549 0.03530 0.02770 -0.0285 1.0000 0.0193
-11.250 -0.9462 0.03380 0.02615 -0.0279 1.0000 0.0195
-11.000 -0.9374 0.03233 0.02463 -0.0272 1.0000 0.0198
-10.750 -0.9281 0.03093 0.02318 -0.0265 1.0000 0.0202
-10.500 -0.9187 0.02957 0.02176 -0.0258 1.0000 0.0205
-10.250 -0.9088 0.02829 0.02043 -0.0250 1.0000 0.0208
-10.000 -0.8988 0.02706 0.01915 -0.0241 1.0000 0.0211
-9.750 -0.8746 0.02582 0.01777 -0.0260 0.8924 0.0218
-9.500 -0.8562 0.02487 0.01662 -0.0261 0.8446 0.0225
-9.250 -0.8442 0.02403 0.01565 -0.0248 0.8252 0.0235
-9.000 -0.8325 0.02328 0.01475 -0.0231 0.8114 0.0245
-8.750 -0.8215 0.02257 0.01395 -0.0211 0.8010 0.0256
-8.500 -0.8091 0.02191 0.01320 -0.0192 0.7932 0.0267
-8.250 -0.7943 0.02129 0.01247 -0.0176 0.7873 0.0284
-8.000 -0.7788 0.02060 0.01173 -0.0162 0.7817 0.0306
-7.750 -0.7618 0.01998 0.01105 -0.0149 0.7767 0.0339
-7.500 -0.7440 0.01937 0.01043 -0.0137 0.7723 0.0392
-7.250 -0.7246 0.01879 0.00985 -0.0127 0.7674 0.0480
-7.000 -0.7051 0.01824 0.00931 -0.0117 0.7630 0.0579
-6.750 -0.6853 0.01770 0.00880 -0.0108 0.7591 0.0714
-6.500 -0.6643 0.01718 0.00833 -0.0100 0.7549 0.0875
-6.250 -0.6443 0.01658 0.00783 -0.0091 0.7508 0.1098
-6.000 -0.6229 0.01610 0.00740 -0.0083 0.7471 0.1331
-5.750 -0.6014 0.01557 0.00698 -0.0076 0.7428 0.1612
-5.500 -0.5807 0.01497 0.00654 -0.0068 0.7382 0.1977
-5.250 -0.5611 0.01429 0.00609 -0.0058 0.7342 0.2521
-5.000 -0.5417 0.01357 0.00570 -0.0048 0.7303 0.3207
-4.750 -0.5212 0.01298 0.00544 -0.0039 0.7259 0.3895
-4.500 -0.4982 0.01267 0.00534 -0.0030 0.7222 0.4422
-4.250 -0.4731 0.01254 0.00531 -0.0024 0.7187 0.4819
-4.000 -0.4470 0.01248 0.00536 -0.0020 0.7145 0.5126
-3.750 -0.4202 0.01248 0.00535 -0.0017 0.7107 0.5351
-3.500 -0.3930 0.01249 0.00535 -0.0013 0.7075 0.5495
-3.250 -0.3652 0.01246 0.00528 -0.0013 0.7034 0.5608
-3.000 -0.3376 0.01248 0.00532 -0.0010 0.6989 0.5722
-2.750 -0.3100 0.01249 0.00529 -0.0008 0.6951 0.5833
-2.500 -0.2821 0.01251 0.00530 -0.0006 0.6910 0.5927
-2.250 -0.2540 0.01249 0.00524 -0.0006 0.6865 0.6005
-2.000 -0.2260 0.01250 0.00525 -0.0004 0.6826 0.6063
-1.750 -0.1979 0.01251 0.00519 -0.0003 0.6792 0.6136
-1.500 -0.1697 0.01251 0.00519 -0.0002 0.6747 0.6195
-1.250 -0.1414 0.01254 0.00522 -0.0002 0.6709 0.6248
-1.000 -0.1132 0.01256 0.00518 -0.0001 0.6677 0.6316
-0.750 -0.0849 0.01257 0.00516 0.0000 0.6648 0.6366
-0.500 -0.0566 0.01258 0.00521 0.0000 0.6597 0.6410
-0.250 -0.0282 0.01257 0.00517 0.0000 0.6550 0.6458
0.000 0.0000 0.01255 0.00509 0.0000 0.6509 0.6509
0.250 0.0282 0.01257 0.00517 0.0001 0.6458 0.6550
0.500 0.0565 0.01258 0.00521 0.0001 0.6409 0.6598
0.750 0.0849 0.01257 0.00516 0.0000 0.6366 0.6648
1.000 0.1132 0.01256 0.00518 0.0001 0.6316 0.6677
1.250 0.1414 0.01254 0.00522 0.0002 0.6248 0.6709
1.500 0.1697 0.01251 0.00519 0.0003 0.6195 0.6747
1.750 0.1979 0.01251 0.00519 0.0003 0.6134 0.6792
2.000 0.2259 0.01250 0.00525 0.0004 0.6063 0.6827
2.250 0.2540 0.01249 0.00523 0.0006 0.6005 0.6865
2.500 0.2821 0.01251 0.00530 0.0006 0.5927 0.6910
2.750 0.3100 0.01249 0.00529 0.0008 0.5834 0.6951
3.000 0.3376 0.01248 0.00532 0.0010 0.5723 0.6989
3.250 0.3652 0.01246 0.00528 0.0013 0.5609 0.7033
3.500 0.3930 0.01249 0.00535 0.0013 0.5496 0.7075
3.750 0.4202 0.01248 0.00535 0.0017 0.5353 0.7107
4.000 0.4470 0.01248 0.00536 0.0020 0.5122 0.7144
4.250 0.4731 0.01254 0.00531 0.0024 0.4818 0.7187
4.500 0.4980 0.01268 0.00533 0.0031 0.4404 0.7222
4.750 0.5210 0.01299 0.00544 0.0039 0.3872 0.7259
5.000 0.5416 0.01358 0.00570 0.0048 0.3192 0.7302
5.500 0.5806 0.01498 0.00654 0.0068 0.1965 0.7381
5.750 0.6015 0.01556 0.00698 0.0076 0.1618 0.7427
6.000 0.6230 0.01609 0.00740 0.0083 0.1337 0.7471
6.250 0.6443 0.01658 0.00783 0.0091 0.1097 0.7508
6.500 0.6643 0.01718 0.00833 0.0100 0.0875 0.7549
6.750 0.6854 0.01770 0.00880 0.0108 0.0714 0.7591
7.000 0.7050 0.01825 0.00931 0.0117 0.0573 0.7630
7.250 0.7245 0.01880 0.00986 0.0127 0.0477 0.7674
7.500 0.7440 0.01937 0.01042 0.0137 0.0392 0.7723
7.750 0.7619 0.01998 0.01105 0.0149 0.0339 0.7767
8.000 0.7790 0.02060 0.01172 0.0162 0.0307 0.7817
8.250 0.7945 0.02129 0.01246 0.0176 0.0284 0.7873
8.500 0.8094 0.02191 0.01320 0.0192 0.0267 0.7932
8.750 0.8215 0.02259 0.01396 0.0211 0.0254 0.8009
9.000 0.8328 0.02328 0.01476 0.0231 0.0244 0.8113
9.250 0.8442 0.02406 0.01567 0.0248 0.0237 0.8253
9.500 0.8564 0.02488 0.01664 0.0261 0.0227 0.8446
9.750 0.8748 0.02583 0.01779 0.0259 0.0219 0.8927
10.000 0.8991 0.02706 0.01914 0.0240 0.0213 1.0000
10.250 0.9093 0.02828 0.02042 0.0249 0.0208 1.0000
10.500 0.9191 0.02957 0.02177 0.0257 0.0205 1.0000
10.750 0.9289 0.03091 0.02315 0.0264 0.0203 1.0000
11.000 0.9381 0.03231 0.02461 0.0271 0.0199 1.0000
11.250 0.9470 0.03378 0.02613 0.0278 0.0197 1.0000
11.500 0.9558 0.03527 0.02768 0.0284 0.0194 1.0000
11.750 0.9640 0.03686 0.02931 0.0289 0.0191 1.0000
12.000 0.9720 0.03849 0.03100 0.0294 0.0191 1.0000
12.250 0.9792 0.04022 0.03277 0.0298 0.0188 1.0000
12.500 0.9862 0.04200 0.03461 0.0301 0.0187 1.0000
12.750 0.9925 0.04389 0.03654 0.0304 0.0185 1.0000
13.000 0.9986 0.04585 0.03855 0.0306 0.0184 1.0000
13.250 1.0045 0.04791 0.04071 0.0308 0.0182 1.0000
13.500 1.0102 0.05000 0.04289 0.0309 0.0182 1.0000
13.750 1.0146 0.05231 0.04532 0.0309 0.0181 1.0000
14.000 1.0185 0.05471 0.04783 0.0307 0.0180 1.0000
14.250 1.0214 0.05727 0.05050 0.0304 0.0180 1.0000
14.500 1.0226 0.06011 0.05348 0.0299 0.0179 1.0000
14.750 1.0223 0.06324 0.05675 0.0292 0.0178 1.0000
15.000 1.0206 0.06665 0.06032 0.0282 0.0177 1.0000
15.250 1.0183 0.07027 0.06409 0.0270 0.0177 1.0000
15.500 1.0124 0.07456 0.06855 0.0253 0.0176 1.0000
15.750 1.0058 0.07912 0.07328 0.0233 0.0176 1.0000
16.000 0.9974 0.08415 0.07849 0.0209 0.0176 1.0000
16.250 0.9849 0.09011 0.08463 0.0178 0.0176 1.0000
16.500 0.9696 0.09689 0.09162 0.0140 0.0176 1.0000
16.750 0.9521 0.10439 0.09932 0.0096 0.0177 1.0000
17.000 0.9324 0.11277 0.10790 0.0045 0.0178 1.0000
17.250 0.8993 0.12478 0.12017 -0.0030 0.0179 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 71-L-150/30 AIRFOIL (fx711530-il)