BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il) Reynolds number: 200,000 Max Cl/Cd: 69.65 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx69h083-il-200000.txt Download as CSV file: xf-fx69h083-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: BELL/WORTMANN FX 69-H-083 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4963 0.09259 0.08942 -0.0061 1.0000 0.0315
-8.000 -0.4933 0.08863 0.08550 -0.0091 1.0000 0.0323
-7.750 -0.4911 0.08446 0.08137 -0.0130 1.0000 0.0331
-7.500 -0.4863 0.07994 0.07686 -0.0180 1.0000 0.0341
-7.250 -0.4779 0.07514 0.07204 -0.0233 1.0000 0.0354
-7.000 -0.4638 0.07012 0.06690 -0.0302 1.0000 0.0373
-6.750 -0.4472 0.06632 0.06283 -0.0350 1.0000 0.0382
-6.500 -0.4358 0.06286 0.05916 -0.0361 1.0000 0.0384
-6.250 -0.4388 0.05595 0.05232 -0.0359 1.0000 0.0395
-6.000 -0.4388 0.05342 0.04984 -0.0333 1.0000 0.0405
-5.750 -0.4397 0.05144 0.04785 -0.0304 1.0000 0.0415
-5.500 -0.4388 0.04940 0.04575 -0.0278 1.0000 0.0429
-5.250 -0.4066 0.04534 0.04141 -0.0314 0.9953 0.0477
-5.000 -0.3739 0.04020 0.03573 -0.0348 0.9893 0.0531
-4.750 -0.3422 0.03702 0.03250 -0.0376 0.9850 0.0576
-4.500 -0.3082 0.03348 0.02851 -0.0401 0.9801 0.0681
-4.250 -0.2756 0.03091 0.02572 -0.0424 0.9747 0.0823
-4.000 -0.2388 0.02826 0.02279 -0.0450 0.9709 0.0963
-3.750 -0.1953 0.02123 0.01430 -0.0431 0.9667 0.0408
-3.500 -0.1588 0.01951 0.01218 -0.0439 0.9606 0.0392
-3.250 -0.1225 0.01744 0.00996 -0.0457 0.9562 0.0431
-3.000 -0.0918 0.01607 0.00840 -0.0457 0.9480 0.0435
-2.750 -0.0599 0.01500 0.00725 -0.0461 0.9417 0.0459
-2.500 -0.0337 0.01445 0.00663 -0.0454 0.9319 0.0504
-2.250 -0.0100 0.01355 0.00575 -0.0443 0.9227 0.0557
-2.000 0.0146 0.01306 0.00519 -0.0432 0.9147 0.0645
-1.750 0.0311 0.01129 0.00453 -0.0413 0.9041 0.3208
-1.500 0.1265 0.00954 0.00462 -0.0530 0.9082 1.0000
-1.250 0.1476 0.00954 0.00446 -0.0515 0.8962 1.0000
-1.000 0.1688 0.00953 0.00431 -0.0499 0.8849 1.0000
-0.750 0.1902 0.00952 0.00414 -0.0483 0.8742 1.0000
-0.500 0.2132 0.00951 0.00402 -0.0473 0.8626 1.0000
-0.250 0.2363 0.00950 0.00391 -0.0462 0.8514 1.0000
0.000 0.2594 0.00949 0.00380 -0.0450 0.8404 1.0000
0.250 0.2825 0.00947 0.00369 -0.0439 0.8299 1.0000
0.500 0.3060 0.00945 0.00358 -0.0428 0.8192 1.0000
0.750 0.3303 0.00946 0.00352 -0.0420 0.8074 1.0000
1.000 0.3548 0.00947 0.00347 -0.0412 0.7958 1.0000
1.250 0.3792 0.00948 0.00343 -0.0403 0.7839 1.0000
1.500 0.4035 0.00948 0.00338 -0.0394 0.7710 1.0000
1.750 0.4279 0.00949 0.00333 -0.0385 0.7572 1.0000
2.000 0.4527 0.00951 0.00330 -0.0378 0.7437 1.0000
2.250 0.4777 0.00955 0.00331 -0.0371 0.7306 1.0000
2.500 0.5027 0.00960 0.00335 -0.0364 0.7162 1.0000
2.750 0.5277 0.00965 0.00337 -0.0357 0.7003 1.0000
3.000 0.5526 0.00970 0.00340 -0.0350 0.6839 1.0000
3.250 0.5777 0.00979 0.00346 -0.0343 0.6681 1.0000
3.500 0.6029 0.00990 0.00359 -0.0338 0.6517 1.0000
3.750 0.6282 0.01003 0.00373 -0.0332 0.6351 1.0000
4.000 0.6535 0.01017 0.00389 -0.0327 0.6181 1.0000
4.250 0.6785 0.01033 0.00406 -0.0321 0.6004 1.0000
4.500 0.7035 0.01051 0.00425 -0.0315 0.5806 1.0000
4.750 0.7282 0.01071 0.00449 -0.0309 0.5583 1.0000
5.000 0.7529 0.01092 0.00472 -0.0302 0.5331 1.0000
5.250 0.7766 0.01115 0.00492 -0.0294 0.4978 1.0000
5.500 0.7981 0.01156 0.00511 -0.0283 0.4355 1.0000
5.750 0.8188 0.01219 0.00546 -0.0273 0.3645 1.0000
6.000 0.8357 0.01340 0.00612 -0.0261 0.2397 1.0000
6.250 0.8410 0.01657 0.00795 -0.0237 0.0442 1.0000
6.500 0.8584 0.01801 0.00948 -0.0221 0.0336 1.0000
6.750 0.8770 0.01920 0.01080 -0.0206 0.0300 1.0000
7.000 0.8942 0.02051 0.01217 -0.0192 0.0267 1.0000
7.250 0.9079 0.02262 0.01431 -0.0173 0.0240 1.0000
7.500 0.9278 0.02417 0.01598 -0.0159 0.0232 1.0000
7.750 0.9489 0.02607 0.01801 -0.0146 0.0226 1.0000
8.000 0.9711 0.02838 0.02056 -0.0135 0.0225 1.0000
8.250 0.9926 0.03123 0.02369 -0.0123 0.0228 1.0000
8.500 1.0111 0.03498 0.02778 -0.0110 0.0235 1.0000
8.750 1.0313 0.03852 0.03156 -0.0099 0.0251 1.0000
9.000 1.0417 0.04353 0.03751 -0.0062 0.0315 1.0000
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Polar data table (+)
Polar graphs
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