BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il) Reynolds number: 100,000 Max Cl/Cd: 52.36 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx69h083-il-100000-n5.txt Download as CSV file: xf-fx69h083-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4808 0.09437 0.08989 -0.0101 1.0000 0.0380
-8.000 -0.4782 0.09040 0.08597 -0.0130 1.0000 0.0384
-7.750 -0.4764 0.08629 0.08192 -0.0165 1.0000 0.0387
-7.500 -0.4727 0.08194 0.07759 -0.0206 1.0000 0.0388
-7.000 -0.4582 0.07144 0.06701 -0.0290 1.0000 0.0287
-6.750 -0.4503 0.06667 0.06219 -0.0316 1.0000 0.0265
-6.500 -0.4411 0.06195 0.05738 -0.0339 1.0000 0.0255
-6.250 -0.4318 0.05781 0.05313 -0.0351 1.0000 0.0256
-6.000 -0.4245 0.05422 0.04941 -0.0349 1.0000 0.0262
-5.750 -0.4200 0.05100 0.04604 -0.0335 1.0000 0.0266
-5.500 -0.4133 0.04766 0.04251 -0.0321 0.9991 0.0266
-5.250 -0.3841 0.04232 0.03673 -0.0350 0.9907 0.0256
-5.000 -0.3536 0.03723 0.03110 -0.0370 0.9834 0.0246
-4.750 -0.3213 0.03284 0.02611 -0.0387 0.9774 0.0244
-4.500 -0.2904 0.02938 0.02206 -0.0396 0.9702 0.0248
-4.250 -0.2578 0.02690 0.01901 -0.0407 0.9639 0.0275
-4.000 -0.2246 0.02469 0.01622 -0.0414 0.9574 0.0305
-3.750 -0.1920 0.02264 0.01369 -0.0419 0.9508 0.0316
-3.500 -0.1597 0.02074 0.01149 -0.0425 0.9443 0.0333
-3.250 -0.1299 0.01965 0.01034 -0.0431 0.9367 0.0393
-3.000 -0.0993 0.01851 0.00905 -0.0434 0.9296 0.0418
-2.750 -0.0720 0.01763 0.00804 -0.0430 0.9209 0.0440
-2.500 -0.0445 0.01682 0.00709 -0.0428 0.9131 0.0479
-2.250 -0.0184 0.01627 0.00643 -0.0423 0.9036 0.0562
-2.000 0.0070 0.01559 0.00587 -0.0417 0.8942 0.0890
-1.750 0.0275 0.01354 0.00550 -0.0409 0.8865 0.4889
-1.500 0.1268 0.01244 0.00536 -0.0532 0.8894 1.0000
-1.250 0.1505 0.01246 0.00517 -0.0523 0.8781 1.0000
-1.000 0.1741 0.01248 0.00501 -0.0514 0.8671 1.0000
-0.750 0.1976 0.01250 0.00484 -0.0505 0.8565 1.0000
-0.500 0.2211 0.01251 0.00470 -0.0495 0.8459 1.0000
-0.250 0.2445 0.01254 0.00460 -0.0485 0.8339 1.0000
0.000 0.2680 0.01257 0.00451 -0.0475 0.8220 1.0000
0.250 0.2916 0.01260 0.00443 -0.0466 0.8104 1.0000
0.500 0.3154 0.01263 0.00437 -0.0456 0.7994 1.0000
0.750 0.3392 0.01266 0.00432 -0.0447 0.7888 1.0000
1.000 0.3634 0.01272 0.00431 -0.0439 0.7775 1.0000
1.250 0.3876 0.01278 0.00435 -0.0431 0.7656 1.0000
1.500 0.4119 0.01284 0.00437 -0.0423 0.7535 1.0000
1.750 0.4361 0.01291 0.00440 -0.0415 0.7410 1.0000
2.000 0.4604 0.01298 0.00444 -0.0406 0.7280 1.0000
2.250 0.4848 0.01305 0.00452 -0.0398 0.7144 1.0000
2.500 0.5090 0.01312 0.00458 -0.0390 0.6993 1.0000
2.750 0.5334 0.01320 0.00465 -0.0381 0.6837 1.0000
3.000 0.5579 0.01330 0.00475 -0.0373 0.6682 1.0000
3.250 0.5825 0.01341 0.00492 -0.0365 0.6526 1.0000
3.500 0.6071 0.01354 0.00506 -0.0358 0.6357 1.0000
3.750 0.6316 0.01369 0.00525 -0.0350 0.6168 1.0000
4.000 0.6560 0.01385 0.00543 -0.0342 0.5978 1.0000
4.250 0.6804 0.01404 0.00566 -0.0335 0.5777 1.0000
4.500 0.7049 0.01426 0.00598 -0.0328 0.5576 1.0000
4.750 0.7293 0.01450 0.00629 -0.0321 0.5376 1.0000
5.000 0.7538 0.01476 0.00666 -0.0314 0.5168 1.0000
5.250 0.7779 0.01504 0.00703 -0.0307 0.4939 1.0000
5.500 0.8017 0.01536 0.00744 -0.0299 0.4687 1.0000
5.750 0.8246 0.01575 0.00788 -0.0290 0.4347 1.0000
6.000 0.8422 0.01650 0.00834 -0.0273 0.3493 1.0000
6.250 0.8523 0.01836 0.00914 -0.0255 0.1745 1.0000
6.500 0.8636 0.02049 0.01053 -0.0239 0.0793 1.0000
6.750 0.8784 0.02221 0.01204 -0.0222 0.0371 1.0000
7.000 0.8943 0.02367 0.01356 -0.0207 0.0272 1.0000
7.250 0.9105 0.02502 0.01511 -0.0191 0.0237 1.0000
7.500 0.9244 0.02657 0.01681 -0.0174 0.0215 1.0000
7.750 0.9347 0.02867 0.01904 -0.0152 0.0200 1.0000
8.000 0.9513 0.03021 0.02073 -0.0137 0.0185 1.0000
8.250 0.9686 0.03181 0.02252 -0.0123 0.0165 1.0000
8.500 0.9860 0.03381 0.02482 -0.0109 0.0154 1.0000
8.750 1.0038 0.03617 0.02741 -0.0096 0.0148 1.0000
9.000 1.0203 0.03879 0.03032 -0.0083 0.0144 1.0000
9.250 1.0342 0.04166 0.03353 -0.0068 0.0140 1.0000
9.500 1.0439 0.04475 0.03699 -0.0051 0.0138 1.0000
9.750 1.0492 0.04802 0.04063 -0.0032 0.0137 1.0000
10.000 1.0497 0.05140 0.04439 -0.0012 0.0136 1.0000
10.250 1.0441 0.05472 0.04804 0.0012 0.0136 1.0000
10.500 1.0342 0.05812 0.05174 0.0033 0.0137 1.0000
10.750 1.0218 0.06180 0.05569 0.0046 0.0137 1.0000
11.000 1.0071 0.06589 0.06004 0.0050 0.0137 1.0000
11.250 0.9902 0.07060 0.06500 0.0043 0.0138 1.0000
11.500 0.9715 0.07604 0.07067 0.0024 0.0140 1.0000
11.750 0.9515 0.08235 0.07718 -0.0008 0.0141 1.0000
12.000 0.9307 0.08965 0.08465 -0.0052 0.0143 1.0000
12.250 0.9098 0.09805 0.09319 -0.0108 0.0146 1.0000
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Polar data table (+)
Polar graphs
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