WORTMANN FX 76-120 (fx76120-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: WORTMANN FX 76-120 (fx76120-il) Reynolds number: 500,000 Max Cl/Cd: 64.19 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx76120-il-500000-n5.txt Download as CSV file: xf-fx76120-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 76-120
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.1345 0.09256 0.08858 -0.0189 1.0000 0.0154
-17.500 -1.1536 0.08573 0.08163 -0.0223 1.0000 0.0155
-17.250 -1.1734 0.07889 0.07468 -0.0258 1.0000 0.0156
-17.000 -1.1935 0.07214 0.06779 -0.0293 1.0000 0.0155
-16.750 -1.2087 0.06616 0.06168 -0.0324 1.0000 0.0157
-16.500 -1.2256 0.06002 0.05541 -0.0356 1.0000 0.0158
-16.250 -1.2358 0.05499 0.05025 -0.0382 1.0000 0.0159
-16.000 -1.2466 0.05003 0.04516 -0.0407 1.0000 0.0161
-15.750 -1.2515 0.04611 0.04110 -0.0425 1.0000 0.0163
-15.500 -1.2545 0.04264 0.03751 -0.0439 1.0000 0.0166
-15.250 -1.2558 0.03960 0.03435 -0.0447 1.0000 0.0170
-15.000 -1.2569 0.03681 0.03144 -0.0451 1.0000 0.0172
-14.750 -1.2555 0.03451 0.02902 -0.0451 1.0000 0.0175
-14.500 -1.2524 0.03255 0.02694 -0.0446 1.0000 0.0178
-14.250 -1.2492 0.03075 0.02505 -0.0437 1.0000 0.0182
-14.000 -1.2468 0.02905 0.02327 -0.0425 1.0000 0.0186
-13.750 -1.2409 0.02771 0.02187 -0.0410 1.0000 0.0190
-13.500 -1.2345 0.02651 0.02059 -0.0393 1.0000 0.0194
-13.250 -1.2255 0.02555 0.01955 -0.0376 1.0000 0.0200
-13.000 -1.2164 0.02465 0.01858 -0.0356 1.0000 0.0206
-12.750 -1.2057 0.02390 0.01774 -0.0336 1.0000 0.0213
-12.500 -1.1961 0.02315 0.01690 -0.0312 1.0000 0.0217
-12.250 -1.1887 0.02234 0.01607 -0.0284 1.0000 0.0225
-12.000 -1.1796 0.02169 0.01537 -0.0256 1.0000 0.0231
-11.750 -1.1684 0.02109 0.01472 -0.0231 1.0000 0.0239
-11.500 -1.1541 0.02052 0.01410 -0.0210 1.0000 0.0247
-11.250 -1.1391 0.01999 0.01350 -0.0190 1.0000 0.0255
-11.000 -1.1234 0.01947 0.01292 -0.0171 1.0000 0.0264
-10.750 -1.1087 0.01887 0.01229 -0.0151 1.0000 0.0275
-10.500 -1.0924 0.01837 0.01176 -0.0132 1.0000 0.0286
-10.250 -1.0756 0.01789 0.01124 -0.0114 1.0000 0.0297
-10.000 -1.0580 0.01748 0.01077 -0.0096 1.0000 0.0309
-9.750 -1.0413 0.01700 0.01027 -0.0077 1.0000 0.0321
-9.500 -1.0246 0.01653 0.00978 -0.0058 1.0000 0.0336
-9.250 -1.0071 0.01613 0.00936 -0.0039 1.0000 0.0352
-9.000 -0.9894 0.01577 0.00895 -0.0021 1.0000 0.0366
-8.750 -0.9722 0.01538 0.00854 -0.0001 1.0000 0.0382
-8.500 -0.9555 0.01498 0.00813 0.0019 1.0000 0.0403
-8.250 -0.9381 0.01465 0.00778 0.0038 1.0000 0.0427
-8.000 -0.9205 0.01434 0.00745 0.0058 1.0000 0.0447
-7.750 -0.8900 0.01390 0.00702 0.0049 0.9981 0.0488
-7.500 -0.8588 0.01356 0.00666 0.0040 0.9955 0.0530
-7.250 -0.8285 0.01314 0.00627 0.0032 0.9926 0.0588
-7.000 -0.7967 0.01275 0.00591 0.0022 0.9895 0.0659
-6.750 -0.7645 0.01239 0.00557 0.0011 0.9866 0.0742
-6.500 -0.7337 0.01202 0.00525 0.0003 0.9829 0.0845
-6.250 -0.7018 0.01164 0.00494 -0.0008 0.9804 0.0978
-6.000 -0.6711 0.01129 0.00465 -0.0015 0.9774 0.1124
-5.750 -0.6419 0.01097 0.00440 -0.0019 0.9731 0.1273
-5.500 -0.6098 0.01067 0.00417 -0.0029 0.9702 0.1429
-5.250 -0.5789 0.01041 0.00395 -0.0036 0.9664 0.1564
-5.000 -0.5477 0.01017 0.00376 -0.0044 0.9620 0.1688
-4.750 -0.5115 0.00992 0.00355 -0.0062 0.9582 0.1825
-4.500 -0.4788 0.00968 0.00335 -0.0072 0.9510 0.1954
-4.250 -0.4438 0.00943 0.00316 -0.0087 0.9447 0.2107
-4.000 -0.4128 0.00921 0.00300 -0.0093 0.9374 0.2254
-3.750 -0.3803 0.00900 0.00283 -0.0103 0.9300 0.2407
-3.500 -0.3504 0.00881 0.00269 -0.0106 0.9201 0.2561
-3.250 -0.3194 0.00861 0.00253 -0.0112 0.9076 0.2729
-3.000 -0.2902 0.00844 0.00239 -0.0113 0.8922 0.2904
-2.750 -0.2624 0.00829 0.00226 -0.0112 0.8759 0.3080
-2.500 -0.2356 0.00815 0.00214 -0.0108 0.8584 0.3256
-2.250 -0.2098 0.00802 0.00203 -0.0102 0.8395 0.3455
-2.000 -0.1845 0.00790 0.00193 -0.0094 0.8161 0.3672
-1.750 -0.1600 0.00782 0.00183 -0.0085 0.7893 0.3896
-1.500 -0.1364 0.00775 0.00175 -0.0074 0.7607 0.4138
-1.250 -0.1130 0.00771 0.00168 -0.0063 0.7306 0.4372
-1.000 -0.0898 0.00767 0.00162 -0.0052 0.7017 0.4614
-0.750 -0.0672 0.00763 0.00158 -0.0039 0.6723 0.4905
-0.500 -0.0450 0.00760 0.00155 -0.0025 0.6414 0.5212
-0.250 -0.0226 0.00761 0.00153 -0.0012 0.6101 0.5496
0.000 0.0000 0.00761 0.00153 0.0000 0.5795 0.5792
0.250 0.0226 0.00761 0.00153 0.0012 0.5494 0.6102
0.500 0.0450 0.00761 0.00155 0.0025 0.5206 0.6410
0.750 0.0674 0.00764 0.00158 0.0038 0.4902 0.6702
1.000 0.0896 0.00767 0.00162 0.0052 0.4610 0.7027
1.250 0.1128 0.00770 0.00168 0.0063 0.4373 0.7326
1.500 0.1363 0.00776 0.00175 0.0074 0.4135 0.7607
1.750 0.1601 0.00782 0.00183 0.0085 0.3900 0.7878
2.000 0.1846 0.00790 0.00193 0.0094 0.3673 0.8161
2.250 0.2098 0.00801 0.00203 0.0102 0.3457 0.8392
2.500 0.2357 0.00815 0.00214 0.0108 0.3256 0.8581
2.750 0.2624 0.00829 0.00226 0.0112 0.3076 0.8756
3.000 0.2902 0.00844 0.00239 0.0113 0.2905 0.8925
3.250 0.3195 0.00861 0.00253 0.0112 0.2730 0.9077
3.500 0.3503 0.00881 0.00269 0.0106 0.2562 0.9200
3.750 0.3806 0.00900 0.00284 0.0102 0.2418 0.9301
4.000 0.4129 0.00921 0.00300 0.0093 0.2256 0.9376
4.250 0.4436 0.00943 0.00316 0.0087 0.2102 0.9446
4.500 0.4789 0.00968 0.00335 0.0071 0.1953 0.9510
4.750 0.5116 0.00992 0.00355 0.0061 0.1826 0.9583
5.000 0.5478 0.01017 0.00376 0.0043 0.1690 0.9620
5.250 0.5789 0.01041 0.00395 0.0036 0.1559 0.9664
5.500 0.6098 0.01067 0.00417 0.0029 0.1421 0.9702
5.750 0.6418 0.01097 0.00440 0.0019 0.1273 0.9731
6.000 0.6712 0.01128 0.00465 0.0015 0.1132 0.9773
6.250 0.7019 0.01164 0.00494 0.0008 0.0979 0.9804
6.500 0.7338 0.01202 0.00525 -0.0003 0.0847 0.9830
6.750 0.7645 0.01239 0.00557 -0.0011 0.0741 0.9866
7.000 0.7968 0.01277 0.00592 -0.0022 0.0652 0.9896
7.250 0.8286 0.01314 0.00627 -0.0032 0.0586 0.9926
7.500 0.8589 0.01355 0.00665 -0.0040 0.0532 0.9956
7.750 0.8901 0.01390 0.00702 -0.0049 0.0490 0.9981
8.000 0.9205 0.01434 0.00744 -0.0058 0.0448 1.0000
8.250 0.9380 0.01465 0.00778 -0.0038 0.0427 1.0000
8.500 0.9554 0.01498 0.00814 -0.0019 0.0405 1.0000
8.750 0.9721 0.01539 0.00854 0.0001 0.0381 1.0000
9.000 0.9894 0.01577 0.00895 0.0021 0.0366 1.0000
9.250 1.0071 0.01613 0.00936 0.0039 0.0351 1.0000
9.500 1.0246 0.01653 0.00978 0.0058 0.0336 1.0000
9.750 1.0414 0.01700 0.01026 0.0077 0.0321 1.0000
10.000 1.0581 0.01747 0.01077 0.0096 0.0308 1.0000
10.250 1.0756 0.01789 0.01124 0.0114 0.0297 1.0000
10.500 1.0927 0.01835 0.01174 0.0132 0.0285 1.0000
10.750 1.1089 0.01886 0.01228 0.0150 0.0274 1.0000
11.000 1.1234 0.01948 0.01292 0.0171 0.0263 1.0000
11.250 1.1393 0.01998 0.01349 0.0190 0.0255 1.0000
11.500 1.1544 0.02051 0.01409 0.0210 0.0246 1.0000
11.750 1.1686 0.02110 0.01473 0.0230 0.0239 1.0000
12.000 1.1797 0.02170 0.01537 0.0256 0.0232 1.0000
12.250 1.1889 0.02235 0.01607 0.0284 0.0225 1.0000
12.500 1.1956 0.02319 0.01696 0.0313 0.0219 1.0000
12.750 1.2071 0.02385 0.01769 0.0334 0.0212 1.0000
13.000 1.2166 0.02467 0.01860 0.0355 0.0206 1.0000
13.250 1.2256 0.02558 0.01959 0.0375 0.0201 1.0000
13.500 1.2342 0.02657 0.02065 0.0393 0.0195 1.0000
13.750 1.2416 0.02771 0.02187 0.0409 0.0190 1.0000
14.000 1.2470 0.02908 0.02332 0.0424 0.0187 1.0000
14.250 1.2510 0.03068 0.02498 0.0436 0.0182 1.0000
14.500 1.2539 0.03250 0.02689 0.0444 0.0178 1.0000
14.750 1.2570 0.03446 0.02898 0.0449 0.0175 1.0000
15.000 1.2576 0.03686 0.03149 0.0450 0.0173 1.0000
15.250 1.2587 0.03940 0.03414 0.0446 0.0170 1.0000
15.500 1.2568 0.04250 0.03737 0.0437 0.0166 1.0000
15.750 1.2537 0.04599 0.04098 0.0423 0.0164 1.0000
16.000 1.2473 0.05013 0.04525 0.0404 0.0161 1.0000
16.250 1.2388 0.05478 0.05004 0.0380 0.0159 1.0000
16.500 1.2271 0.06007 0.05546 0.0353 0.0157 1.0000
16.750 1.2116 0.06599 0.06151 0.0321 0.0157 1.0000
17.000 1.1954 0.07215 0.06780 0.0289 0.0155 1.0000
17.250 1.1748 0.07900 0.07478 0.0254 0.0155 1.0000
17.500 1.1561 0.08569 0.08158 0.0220 0.0154 1.0000
|
Polar data table (+)
Polar graphs
<< Back to WORTMANN FX 76-120 (fx76120-il)