FX 71-L-150/25 AIRFOIL (fx711525-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 71-L-150/25 AIRFOIL (fx711525-il) Reynolds number: 500,000 Max Cl/Cd: 50.46 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx711525-il-500000.txt Download as CSV file: xf-fx711525-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 71-L-150/25 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
------ -------- --------- --------- -------- -------- --------
-17.500 -0.8317 0.14602 0.14332 0.0147 1.0000 0.0211
-17.250 -0.8349 0.14073 0.13803 0.0120 1.0000 0.0208
-17.000 -0.9106 0.11729 0.11431 -0.0027 1.0000 0.0201
-16.750 -0.9689 0.10062 0.09730 -0.0135 1.0000 0.0196
-16.500 -1.0772 0.07807 0.07388 -0.0270 1.0000 0.0185
-16.250 -1.0952 0.07217 0.06777 -0.0298 1.0000 0.0185
-16.000 -1.1080 0.06748 0.06287 -0.0319 1.0000 0.0184
-15.750 -1.1169 0.06356 0.05878 -0.0333 1.0000 0.0183
-15.500 -1.1192 0.06037 0.05547 -0.0339 1.0000 0.0182
-15.250 -1.1281 0.05649 0.05141 -0.0346 1.0000 0.0183
-15.000 -1.1285 0.05379 0.04858 -0.0350 1.0000 0.0182
-14.750 -1.1260 0.05119 0.04587 -0.0350 1.0000 0.0182
-14.500 -1.1260 0.04856 0.04309 -0.0349 1.0000 0.0182
-14.250 -1.1227 0.04621 0.04061 -0.0347 1.0000 0.0182
-14.000 -1.1163 0.04416 0.03846 -0.0343 1.0000 0.0182
-13.750 -1.1087 0.04221 0.03641 -0.0339 1.0000 0.0182
-13.500 -1.1004 0.04035 0.03445 -0.0334 1.0000 0.0183
-13.250 -1.0899 0.03872 0.03274 -0.0328 1.0000 0.0183
-13.000 -1.0782 0.03716 0.03112 -0.0321 1.0000 0.0183
-12.750 -1.0661 0.03567 0.02957 -0.0314 1.0000 0.0183
-12.500 -1.0538 0.03424 0.02810 -0.0307 1.0000 0.0184
-12.250 -1.0415 0.03293 0.02673 -0.0300 1.0000 0.0184
-12.000 -1.0296 0.03158 0.02536 -0.0292 1.0000 0.0184
-11.750 -1.0176 0.03030 0.02404 -0.0284 1.0000 0.0185
-11.500 -1.0063 0.02898 0.02270 -0.0276 1.0000 0.0186
-11.250 -0.9950 0.02770 0.02139 -0.0267 1.0000 0.0186
-11.000 -0.9836 0.02648 0.02015 -0.0259 1.0000 0.0187
-10.750 -0.9446 0.02497 0.01852 -0.0308 0.9022 0.0188
-10.500 -0.9300 0.02409 0.01743 -0.0303 0.8579 0.0190
-10.250 -0.9211 0.02315 0.01636 -0.0287 0.8431 0.0192
-10.000 -0.9113 0.02224 0.01536 -0.0272 0.8338 0.0192
-9.750 -0.9031 0.02135 0.01437 -0.0253 0.8263 0.0194
-9.500 -0.8935 0.02057 0.01354 -0.0233 0.8204 0.0197
-9.250 -0.8838 0.01989 0.01280 -0.0211 0.8145 0.0198
-9.000 -0.8743 0.01932 0.01215 -0.0186 0.8090 0.0201
-8.750 -0.8606 0.01873 0.01150 -0.0167 0.8042 0.0203
-8.500 -0.8445 0.01815 0.01087 -0.0152 0.7997 0.0204
-8.250 -0.8270 0.01761 0.01027 -0.0139 0.7952 0.0208
-8.000 -0.8082 0.01715 0.00973 -0.0127 0.7909 0.0210
-7.750 -0.7888 0.01663 0.00918 -0.0116 0.7869 0.0214
-7.500 -0.7683 0.01614 0.00868 -0.0106 0.7828 0.0220
-7.250 -0.7464 0.01574 0.00824 -0.0098 0.7790 0.0228
-7.000 -0.7239 0.01539 0.00783 -0.0091 0.7755 0.0239
-6.750 -0.7013 0.01498 0.00742 -0.0083 0.7720 0.0254
-6.500 -0.6782 0.01455 0.00698 -0.0077 0.7680 0.0284
-6.250 -0.6559 0.01405 0.00651 -0.0069 0.7639 0.0353
-6.000 -0.6345 0.01348 0.00606 -0.0061 0.7601 0.0573
-5.750 -0.6122 0.01296 0.00567 -0.0054 0.7567 0.0846
-5.500 -0.5895 0.01239 0.00529 -0.0048 0.7527 0.1161
-5.250 -0.5667 0.01182 0.00492 -0.0042 0.7486 0.1548
-5.000 -0.5446 0.01119 0.00452 -0.0035 0.7450 0.2071
-4.750 -0.5221 0.01060 0.00415 -0.0029 0.7415 0.2640
-4.500 -0.4991 0.00998 0.00382 -0.0023 0.7374 0.3266
-4.250 -0.4758 0.00942 0.00354 -0.0018 0.7329 0.3909
-4.000 -0.4509 0.00905 0.00335 -0.0013 0.7289 0.4417
-3.750 -0.4252 0.00880 0.00324 -0.0009 0.7251 0.4846
-3.500 -0.3979 0.00871 0.00319 -0.0007 0.7208 0.5113
-3.250 -0.3699 0.00861 0.00313 -0.0006 0.7158 0.5287
-3.000 -0.3419 0.00855 0.00307 -0.0005 0.7111 0.5448
-2.750 -0.3140 0.00849 0.00301 -0.0003 0.7070 0.5601
-2.500 -0.2860 0.00848 0.00297 -0.0002 0.7028 0.5737
-2.250 -0.2576 0.00842 0.00296 -0.0002 0.6982 0.5854
-2.000 -0.2294 0.00839 0.00297 -0.0001 0.6936 0.5970
-1.750 -0.2010 0.00841 0.00297 0.0000 0.6895 0.6091
-1.500 -0.1727 0.00847 0.00302 0.0001 0.6856 0.6201
-1.250 -0.1441 0.00848 0.00304 0.0001 0.6813 0.6287
-1.000 -0.1153 0.00847 0.00307 0.0001 0.6764 0.6353
-0.750 -0.0864 0.00848 0.00305 0.0001 0.6716 0.6417
-0.500 -0.0577 0.00847 0.00300 0.0001 0.6672 0.6473
-0.250 -0.0290 0.00848 0.00304 0.0001 0.6626 0.6523
0.000 0.0000 0.00848 0.00305 0.0000 0.6574 0.6574
0.250 0.0290 0.00848 0.00304 -0.0001 0.6523 0.6626
0.500 0.0577 0.00847 0.00300 -0.0001 0.6473 0.6672
0.750 0.0865 0.00848 0.00305 -0.0001 0.6417 0.6716
1.000 0.1153 0.00847 0.00307 -0.0001 0.6353 0.6764
1.250 0.1441 0.00848 0.00304 -0.0001 0.6287 0.6813
1.500 0.1727 0.00846 0.00302 -0.0001 0.6200 0.6856
1.750 0.2010 0.00841 0.00296 0.0000 0.6087 0.6895
2.000 0.2294 0.00839 0.00297 0.0001 0.5966 0.6936
2.250 0.2576 0.00842 0.00296 0.0002 0.5850 0.6982
2.500 0.2860 0.00848 0.00297 0.0002 0.5737 0.7028
2.750 0.3140 0.00849 0.00300 0.0003 0.5599 0.7070
3.000 0.3419 0.00855 0.00306 0.0005 0.5446 0.7111
3.250 0.3699 0.00861 0.00313 0.0006 0.5286 0.7158
3.500 0.3979 0.00871 0.00319 0.0007 0.5112 0.7208
3.750 0.4251 0.00881 0.00324 0.0009 0.4831 0.7251
4.000 0.4509 0.00905 0.00335 0.0013 0.4415 0.7289
4.250 0.4758 0.00943 0.00355 0.0018 0.3897 0.7329
4.500 0.4992 0.00998 0.00382 0.0023 0.3271 0.7374
4.750 0.5221 0.01060 0.00415 0.0029 0.2635 0.7415
5.000 0.5446 0.01119 0.00452 0.0035 0.2070 0.7450
5.250 0.5668 0.01182 0.00491 0.0042 0.1549 0.7486
5.500 0.5895 0.01239 0.00529 0.0048 0.1160 0.7527
5.750 0.6123 0.01295 0.00567 0.0054 0.0852 0.7567
6.000 0.6345 0.01349 0.00606 0.0061 0.0570 0.7602
6.250 0.6561 0.01404 0.00651 0.0069 0.0357 0.7639
6.500 0.6784 0.01454 0.00697 0.0077 0.0286 0.7680
6.750 0.7014 0.01497 0.00741 0.0083 0.0256 0.7720
7.000 0.7239 0.01539 0.00783 0.0091 0.0239 0.7755
7.250 0.7464 0.01574 0.00824 0.0098 0.0227 0.7790
7.500 0.7683 0.01614 0.00868 0.0106 0.0221 0.7828
7.750 0.7891 0.01661 0.00917 0.0115 0.0215 0.7869
8.000 0.8082 0.01715 0.00974 0.0127 0.0210 0.7909
8.250 0.8270 0.01761 0.01027 0.0139 0.0208 0.7953
8.500 0.8445 0.01815 0.01086 0.0152 0.0205 0.7996
8.750 0.8606 0.01873 0.01150 0.0167 0.0203 0.8042
9.000 0.8743 0.01932 0.01215 0.0185 0.0201 0.8089
9.250 0.8840 0.01989 0.01280 0.0211 0.0199 0.8145
9.500 0.8928 0.02062 0.01359 0.0234 0.0198 0.8204
9.750 0.9028 0.02138 0.01441 0.0253 0.0195 0.8263
10.000 0.9117 0.02223 0.01535 0.0271 0.0194 0.8337
10.250 0.9213 0.02315 0.01636 0.0286 0.0191 0.8430
10.500 0.9312 0.02402 0.01736 0.0301 0.0190 0.8575
10.750 0.9446 0.02498 0.01854 0.0308 0.0188 0.9020
11.000 0.9843 0.02644 0.02012 0.0259 0.0187 1.0000
11.250 0.9955 0.02770 0.02139 0.0267 0.0186 1.0000
11.500 1.0071 0.02894 0.02265 0.0275 0.0186 1.0000
11.750 1.0183 0.03026 0.02401 0.0283 0.0185 1.0000
12.000 1.0302 0.03154 0.02531 0.0291 0.0184 1.0000
12.250 1.0421 0.03296 0.02675 0.0299 0.0183 1.0000
12.500 1.0546 0.03423 0.02809 0.0306 0.0184 1.0000
12.750 1.0672 0.03571 0.02960 0.0314 0.0183 1.0000
13.000 1.0788 0.03719 0.03114 0.0321 0.0182 1.0000
13.250 1.0895 0.03878 0.03282 0.0327 0.0182 1.0000
13.500 1.1013 0.04034 0.03444 0.0333 0.0183 1.0000
13.750 1.1094 0.04216 0.03636 0.0338 0.0182 1.0000
14.000 1.1164 0.04414 0.03845 0.0342 0.0182 1.0000
14.250 1.1223 0.04624 0.04065 0.0346 0.0182 1.0000
14.500 1.1250 0.04859 0.04313 0.0347 0.0182 1.0000
14.750 1.1295 0.05100 0.04565 0.0349 0.0182 1.0000
15.000 1.1317 0.05347 0.04824 0.0349 0.0183 1.0000
15.250 1.1286 0.05670 0.05162 0.0346 0.0182 1.0000
15.500 1.1254 0.05955 0.05462 0.0339 0.0184 1.0000
15.750 1.1182 0.06345 0.05867 0.0331 0.0183 1.0000
16.000 1.1096 0.06740 0.06278 0.0318 0.0183 1.0000
16.250 1.0970 0.07204 0.06763 0.0297 0.0185 1.0000
16.500 1.0758 0.07841 0.07426 0.0266 0.0186 1.0000
16.750 1.0486 0.08626 0.08239 0.0224 0.0188 1.0000
17.000 0.9101 0.11769 0.11472 0.0022 0.0200 1.0000
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