FX 71-L-150/30 AIRFOIL (fx711530-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 71-L-150/30 AIRFOIL (fx711530-il) Reynolds number: 500,000 Max Cl/Cd: 51.77 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx711530-il-500000.txt Download as CSV file: xf-fx711530-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -1.0314 0.09539 0.09164 -0.0184 1.0000 0.0187
-17.000 -1.0560 0.08738 0.08339 -0.0232 1.0000 0.0186
-16.750 -1.0708 0.08151 0.07733 -0.0266 1.0000 0.0185
-16.500 -1.0808 0.07675 0.07243 -0.0291 1.0000 0.0184
-16.250 -1.0902 0.07225 0.06778 -0.0311 1.0000 0.0184
-16.000 -1.0976 0.06807 0.06346 -0.0324 1.0000 0.0184
-15.750 -1.1036 0.06405 0.05931 -0.0333 1.0000 0.0183
-15.500 -1.1120 0.06037 0.05547 -0.0346 1.0000 0.0183
-15.250 -1.1152 0.05718 0.05214 -0.0351 1.0000 0.0183
-15.000 -1.1177 0.05403 0.04884 -0.0354 1.0000 0.0183
-14.750 -1.1163 0.05139 0.04609 -0.0355 1.0000 0.0183
-14.500 -1.1135 0.04895 0.04354 -0.0354 1.0000 0.0183
-14.250 -1.1102 0.04656 0.04102 -0.0352 1.0000 0.0183
-14.000 -1.1040 0.04444 0.03880 -0.0348 1.0000 0.0183
-13.750 -1.0956 0.04258 0.03685 -0.0343 1.0000 0.0182
-13.500 -1.0870 0.04077 0.03496 -0.0338 1.0000 0.0182
-13.250 -1.0786 0.03897 0.03306 -0.0331 1.0000 0.0182
-13.000 -1.0686 0.03738 0.03140 -0.0325 1.0000 0.0183
-12.750 -1.0575 0.03591 0.02988 -0.0318 1.0000 0.0182
-12.500 -1.0470 0.03444 0.02835 -0.0311 1.0000 0.0182
-12.250 -1.0360 0.03304 0.02690 -0.0304 1.0000 0.0182
-12.000 -1.0254 0.03166 0.02545 -0.0296 1.0000 0.0183
-11.750 -1.0144 0.03033 0.02409 -0.0288 1.0000 0.0183
-11.500 -1.0036 0.02901 0.02272 -0.0280 1.0000 0.0184
-11.250 -0.9930 0.02771 0.02139 -0.0271 1.0000 0.0184
-11.000 -0.9847 0.02624 0.01990 -0.0261 1.0000 0.0185
-10.750 -0.9768 0.02480 0.01844 -0.0251 1.0000 0.0187
-10.500 -0.9530 0.02331 0.01690 -0.0272 0.9283 0.0190
-10.250 -0.9273 0.02230 0.01559 -0.0291 0.8423 0.0193
-10.000 -0.9206 0.02145 0.01458 -0.0269 0.8216 0.0194
-9.750 -0.9131 0.02065 0.01368 -0.0247 0.8088 0.0196
-9.500 -0.9048 0.01995 0.01288 -0.0222 0.8001 0.0199
-9.250 -0.8959 0.01934 0.01219 -0.0196 0.7934 0.0202
-9.000 -0.8837 0.01880 0.01156 -0.0175 0.7881 0.0206
-8.750 -0.8679 0.01823 0.01093 -0.0159 0.7832 0.0209
-8.500 -0.8504 0.01773 0.01035 -0.0146 0.7785 0.0213
-8.250 -0.8320 0.01726 0.00981 -0.0133 0.7743 0.0216
-8.000 -0.8137 0.01667 0.00920 -0.0121 0.7702 0.0224
-7.750 -0.7930 0.01622 0.00872 -0.0111 0.7660 0.0232
-7.500 -0.7714 0.01582 0.00827 -0.0103 0.7622 0.0242
-7.250 -0.7497 0.01541 0.00781 -0.0094 0.7584 0.0257
-7.000 -0.7276 0.01496 0.00734 -0.0086 0.7540 0.0280
-6.750 -0.7057 0.01450 0.00687 -0.0078 0.7496 0.0322
-6.500 -0.6846 0.01398 0.00641 -0.0068 0.7455 0.0453
-6.250 -0.6630 0.01341 0.00598 -0.0061 0.7414 0.0667
-6.000 -0.6404 0.01294 0.00560 -0.0054 0.7376 0.0906
-5.750 -0.6184 0.01241 0.00523 -0.0047 0.7343 0.1238
-5.500 -0.5958 0.01190 0.00490 -0.0041 0.7306 0.1613
-5.250 -0.5737 0.01128 0.00452 -0.0034 0.7265 0.2130
-5.000 -0.5510 0.01074 0.00419 -0.0028 0.7227 0.2625
-4.750 -0.5281 0.01023 0.00390 -0.0022 0.7193 0.3174
-4.500 -0.5044 0.00972 0.00364 -0.0016 0.7153 0.3730
-4.250 -0.4793 0.00938 0.00346 -0.0012 0.7116 0.4197
-4.000 -0.4535 0.00915 0.00335 -0.0009 0.7085 0.4610
-3.750 -0.4269 0.00898 0.00330 -0.0006 0.7052 0.4910
-3.500 -0.3992 0.00888 0.00325 -0.0005 0.7012 0.5132
-3.250 -0.3712 0.00882 0.00320 -0.0004 0.6977 0.5298
-3.000 -0.3430 0.00878 0.00314 -0.0003 0.6947 0.5445
-2.750 -0.3148 0.00875 0.00312 -0.0003 0.6908 0.5594
-2.500 -0.2868 0.00871 0.00313 -0.0001 0.6867 0.5743
-2.250 -0.2587 0.00869 0.00313 0.0000 0.6832 0.5879
-2.000 -0.2302 0.00873 0.00309 0.0001 0.6801 0.5990
-1.750 -0.2017 0.00870 0.00314 0.0002 0.6758 0.6070
-1.500 -0.1730 0.00873 0.00314 0.0002 0.6718 0.6154
-1.250 -0.1443 0.00874 0.00315 0.0002 0.6685 0.6216
-0.750 -0.0865 0.00882 0.00318 0.0001 0.6608 0.6325
-0.500 -0.0577 0.00882 0.00320 0.0001 0.6563 0.6375
-0.250 -0.0289 0.00884 0.00321 0.0001 0.6521 0.6424
0.000 0.0000 0.00887 0.00321 0.0000 0.6476 0.6476
0.250 0.0289 0.00884 0.00320 -0.0001 0.6424 0.6521
0.500 0.0577 0.00882 0.00320 -0.0001 0.6374 0.6563
0.750 0.0865 0.00882 0.00318 -0.0001 0.6325 0.6608
1.250 0.1443 0.00874 0.00315 -0.0002 0.6215 0.6685
1.500 0.1730 0.00873 0.00314 -0.0002 0.6154 0.6718
1.750 0.2017 0.00870 0.00314 -0.0002 0.6069 0.6759
2.000 0.2301 0.00873 0.00309 -0.0001 0.5988 0.6801
2.250 0.2586 0.00869 0.00312 0.0000 0.5876 0.6832
2.500 0.2868 0.00871 0.00313 0.0001 0.5744 0.6867
2.750 0.3148 0.00875 0.00312 0.0003 0.5593 0.6908
3.000 0.3431 0.00878 0.00315 0.0003 0.5449 0.6947
3.250 0.3712 0.00882 0.00320 0.0004 0.5300 0.6977
3.500 0.3992 0.00888 0.00325 0.0005 0.5135 0.7012
3.750 0.4269 0.00898 0.00330 0.0006 0.4909 0.7052
4.000 0.4534 0.00915 0.00335 0.0009 0.4606 0.7085
4.250 0.4793 0.00938 0.00346 0.0013 0.4192 0.7116
4.500 0.5042 0.00974 0.00365 0.0017 0.3696 0.7153
4.750 0.5280 0.01025 0.00391 0.0022 0.3151 0.7194
5.000 0.5509 0.01075 0.00419 0.0028 0.2612 0.7227
5.250 0.5736 0.01129 0.00453 0.0034 0.2117 0.7265
5.500 0.5956 0.01191 0.00490 0.0041 0.1606 0.7306
5.750 0.6186 0.01239 0.00522 0.0046 0.1253 0.7343
6.000 0.6405 0.01292 0.00560 0.0054 0.0914 0.7376
6.250 0.6630 0.01342 0.00598 0.0061 0.0664 0.7414
6.500 0.6847 0.01397 0.00641 0.0068 0.0457 0.7455
6.750 0.7057 0.01450 0.00687 0.0078 0.0322 0.7495
7.000 0.7276 0.01496 0.00735 0.0086 0.0277 0.7540
7.250 0.7497 0.01541 0.00781 0.0094 0.0256 0.7584
7.500 0.7715 0.01582 0.00827 0.0102 0.0243 0.7621
7.750 0.7930 0.01622 0.00872 0.0111 0.0233 0.7660
8.000 0.8138 0.01667 0.00920 0.0121 0.0225 0.7702
8.250 0.8323 0.01724 0.00979 0.0133 0.0217 0.7743
8.500 0.8505 0.01772 0.01035 0.0145 0.0213 0.7785
8.750 0.8678 0.01824 0.01094 0.0159 0.0209 0.7832
9.000 0.8838 0.01880 0.01156 0.0175 0.0205 0.7881
9.250 0.8957 0.01935 0.01220 0.0197 0.0204 0.7935
9.500 0.9049 0.01995 0.01289 0.0222 0.0200 0.8001
9.750 0.9129 0.02067 0.01370 0.0247 0.0198 0.8089
10.000 0.9207 0.02145 0.01459 0.0269 0.0196 0.8216
10.250 0.9278 0.02228 0.01557 0.0290 0.0192 0.8425
10.500 0.9534 0.02332 0.01690 0.0272 0.0190 0.9281
10.750 0.9791 0.02467 0.01831 0.0249 0.0189 1.0000
11.000 0.9875 0.02605 0.01972 0.0259 0.0187 1.0000
11.250 0.9964 0.02746 0.02114 0.0268 0.0186 1.0000
11.500 1.0048 0.02895 0.02266 0.0278 0.0184 1.0000
11.750 1.0153 0.03031 0.02406 0.0287 0.0183 1.0000
12.000 1.0264 0.03162 0.02540 0.0295 0.0184 1.0000
12.250 1.0371 0.03301 0.02686 0.0303 0.0182 1.0000
12.500 1.0481 0.03441 0.02831 0.0310 0.0182 1.0000
12.750 1.0586 0.03588 0.02984 0.0317 0.0182 1.0000
13.000 1.0692 0.03740 0.03142 0.0324 0.0182 1.0000
13.250 1.0790 0.03902 0.03312 0.0330 0.0182 1.0000
13.500 1.0889 0.04066 0.03483 0.0336 0.0182 1.0000
13.750 1.0976 0.04250 0.03676 0.0342 0.0182 1.0000
14.000 1.1055 0.04442 0.03877 0.0347 0.0183 1.0000
14.250 1.1124 0.04645 0.04090 0.0351 0.0183 1.0000
14.500 1.1176 0.04873 0.04329 0.0354 0.0183 1.0000
14.750 1.1190 0.05129 0.04597 0.0354 0.0183 1.0000
15.000 1.1166 0.05413 0.04897 0.0351 0.0183 1.0000
15.250 1.1150 0.05707 0.05203 0.0347 0.0183 1.0000
15.500 1.1105 0.06052 0.05564 0.0341 0.0183 1.0000
15.750 1.1058 0.06405 0.05931 0.0333 0.0183 1.0000
16.000 1.0980 0.06796 0.06336 0.0319 0.0183 1.0000
16.250 1.0919 0.07218 0.06770 0.0309 0.0184 1.0000
16.500 1.0819 0.07679 0.07247 0.0289 0.0184 1.0000
16.750 1.0718 0.08157 0.07740 0.0264 0.0185 1.0000
17.000 1.0600 0.08693 0.08291 0.0233 0.0186 1.0000
17.250 1.0216 0.09751 0.09387 0.0167 0.0189 1.0000
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