WORTMANN FX 80-080 (fx80080-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 80-080 (fx80080-il) Reynolds number: 100,000 Max Cl/Cd: 55.16 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx80080-il-100000-n5.txt Download as CSV file: xf-fx80080-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 80-080
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4637 0.12202 0.11673 -0.0272 1.0000 0.0412
-10.250 -0.4651 0.11908 0.11386 -0.0303 1.0000 0.0416
-10.000 -0.4647 0.11585 0.11068 -0.0328 1.0000 0.0418
-9.750 -0.4645 0.11228 0.10718 -0.0350 1.0000 0.0419
-9.500 -0.4585 0.10651 0.10145 -0.0333 1.0000 0.0429
-9.250 -0.4517 0.10274 0.09769 -0.0325 1.0000 0.0438
-9.000 -0.4485 0.09929 0.09428 -0.0330 1.0000 0.0443
-8.750 -0.4471 0.09572 0.09076 -0.0337 1.0000 0.0448
-8.500 -0.3513 0.07429 0.06978 -0.0392 1.0000 0.0402
-8.000 -0.3700 0.06453 0.06014 -0.0416 1.0000 0.0286
-7.750 -0.3778 0.06111 0.05680 -0.0406 1.0000 0.0279
-7.500 -0.3928 0.05831 0.05411 -0.0394 1.0000 0.0276
-7.250 -0.4719 0.07138 0.06676 -0.0436 1.0000 0.0281
-7.000 -0.4769 0.06819 0.06359 -0.0428 1.0000 0.0273
-6.750 -0.4821 0.06509 0.06049 -0.0418 1.0000 0.0267
-6.500 -0.4868 0.06168 0.05702 -0.0409 1.0000 0.0261
-6.250 -0.4881 0.05828 0.05353 -0.0400 1.0000 0.0254
-6.000 -0.4639 0.05214 0.04708 -0.0452 0.9946 0.0244
-5.750 -0.4378 0.04625 0.04079 -0.0493 0.9894 0.0235
-5.500 -0.4123 0.04107 0.03514 -0.0520 0.9839 0.0229
-5.250 -0.3831 0.03629 0.02980 -0.0544 0.9796 0.0226
-5.000 -0.3553 0.03248 0.02543 -0.0557 0.9751 0.0231
-4.750 -0.3263 0.02987 0.02231 -0.0568 0.9709 0.0257
-4.500 -0.2946 0.02735 0.01919 -0.0578 0.9678 0.0278
-4.250 -0.2623 0.02495 0.01619 -0.0587 0.9652 0.0285
-4.000 -0.2347 0.02321 0.01407 -0.0586 0.9608 0.0292
-3.750 -0.2054 0.02123 0.01190 -0.0591 0.9575 0.0310
-3.500 -0.1745 0.01998 0.01057 -0.0599 0.9547 0.0337
-3.250 -0.1415 0.01927 0.00968 -0.0611 0.9523 0.0416
-3.000 -0.1166 0.01823 0.00865 -0.0608 0.9474 0.0474
-2.750 -0.0871 0.01744 0.00781 -0.0613 0.9436 0.0611
-2.500 -0.0554 0.01672 0.00710 -0.0624 0.9407 0.0938
-2.250 -0.0247 0.01556 0.00663 -0.0638 0.9383 0.2345
-2.000 -0.0114 0.01407 0.00684 -0.0610 0.9328 0.6540
-1.750 0.0100 0.01405 0.00698 -0.0586 0.9285 0.7882
-1.500 0.0349 0.01403 0.00695 -0.0570 0.9255 0.8497
-1.250 0.0531 0.01398 0.00688 -0.0539 0.9202 0.9103
-1.000 0.1345 0.01386 0.00661 -0.0639 0.9256 0.9854
-0.750 0.1696 0.01390 0.00650 -0.0661 0.9216 1.0000
-0.500 0.1947 0.01394 0.00641 -0.0661 0.9157 1.0000
-0.250 0.2276 0.01395 0.00632 -0.0676 0.9122 1.0000
0.000 0.2495 0.01406 0.00635 -0.0670 0.9055 1.0000
0.250 0.2795 0.01413 0.00635 -0.0679 0.9009 1.0000
0.500 0.3143 0.01416 0.00634 -0.0696 0.8977 1.0000
0.750 0.3359 0.01434 0.00648 -0.0688 0.8903 1.0000
1.000 0.3683 0.01442 0.00654 -0.0700 0.8862 1.0000
1.250 0.3976 0.01453 0.00665 -0.0706 0.8807 1.0000
1.500 0.4259 0.01464 0.00680 -0.0709 0.8742 1.0000
1.750 0.4624 0.01464 0.00683 -0.0726 0.8701 1.0000
2.000 0.4856 0.01480 0.00704 -0.0719 0.8610 1.0000
2.250 0.5202 0.01478 0.00708 -0.0731 0.8551 1.0000
2.500 0.5478 0.01482 0.00720 -0.0729 0.8453 1.0000
2.750 0.5767 0.01478 0.00730 -0.0728 0.8339 1.0000
3.000 0.6071 0.01461 0.00722 -0.0727 0.8200 1.0000
3.250 0.6397 0.01426 0.00697 -0.0726 0.8018 1.0000
3.500 0.6633 0.01409 0.00688 -0.0710 0.7784 1.0000
3.750 0.6876 0.01392 0.00681 -0.0695 0.7518 1.0000
4.000 0.7129 0.01375 0.00677 -0.0682 0.7188 1.0000
4.250 0.7345 0.01370 0.00677 -0.0662 0.6706 1.0000
4.500 0.7590 0.01376 0.00645 -0.0644 0.5572 1.0000
4.750 0.7693 0.01497 0.00669 -0.0607 0.3868 1.0000
5.000 0.7785 0.01648 0.00740 -0.0577 0.2465 1.0000
5.250 0.7936 0.01773 0.00819 -0.0559 0.1617 1.0000
5.500 0.8106 0.01888 0.00911 -0.0543 0.1122 1.0000
5.750 0.8287 0.01994 0.01004 -0.0529 0.0825 1.0000
6.000 0.8466 0.02104 0.01100 -0.0514 0.0634 1.0000
6.250 0.8653 0.02209 0.01215 -0.0500 0.0524 1.0000
6.500 0.8830 0.02337 0.01356 -0.0482 0.0458 1.0000
6.750 0.9014 0.02471 0.01496 -0.0468 0.0406 1.0000
7.000 0.9214 0.02611 0.01650 -0.0456 0.0348 1.0000
7.250 0.9428 0.02772 0.01826 -0.0446 0.0310 1.0000
7.500 0.9642 0.02983 0.02053 -0.0437 0.0280 1.0000
7.750 0.9863 0.03185 0.02289 -0.0428 0.0237 1.0000
8.000 1.0075 0.03428 0.02568 -0.0417 0.0212 1.0000
8.250 1.0251 0.03682 0.02853 -0.0403 0.0195 1.0000
8.500 1.0373 0.03956 0.03148 -0.0388 0.0177 1.0000
8.750 1.0472 0.04262 0.03508 -0.0364 0.0162 1.0000
9.000 1.0533 0.04601 0.03901 -0.0338 0.0149 1.0000
9.250 1.0532 0.04992 0.04341 -0.0308 0.0146 1.0000
9.500 1.0479 0.05387 0.04777 -0.0276 0.0144 1.0000
9.750 1.0372 0.05759 0.05183 -0.0241 0.0143 1.0000
10.000 1.0225 0.06119 0.05571 -0.0208 0.0143 1.0000
10.250 1.0044 0.06512 0.05988 -0.0183 0.0143 1.0000
10.500 0.9856 0.06934 0.06431 -0.0171 0.0144 1.0000
10.750 0.9653 0.07418 0.06933 -0.0173 0.0145 1.0000
11.000 0.9454 0.07962 0.07493 -0.0189 0.0146 1.0000
11.250 0.9240 0.08637 0.08180 -0.0224 0.0148 1.0000
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Polar data table (+)
Polar graphs
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