BELL/WORTMANN FX 69-H-098 AIRFOIL (fx69h098-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BELL/WORTMANN FX 69-H-098 AIRFOIL (fx69h098-il) Reynolds number: 100,000 Max Cl/Cd: 45.38 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx69h098-il-100000-n5.txt Download as CSV file: xf-fx69h098-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BELL/WORTMANN FX 69-H-098 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5278 0.10183 0.09679 -0.0115 1.0000 0.0375
-9.500 -0.5268 0.09752 0.09251 -0.0130 1.0000 0.0361
-9.250 -0.5286 0.09269 0.08773 -0.0157 1.0000 0.0354
-9.000 -0.5319 0.08754 0.08263 -0.0189 1.0000 0.0349
-8.750 -0.5383 0.08168 0.07682 -0.0236 1.0000 0.0342
-8.500 -0.5524 0.07476 0.06990 -0.0291 1.0000 0.0329
-7.250 -0.5777 0.04891 0.04272 -0.0293 1.0000 0.0297
-7.000 -0.5721 0.04550 0.03906 -0.0274 1.0000 0.0295
-6.750 -0.5647 0.04230 0.03556 -0.0253 1.0000 0.0294
-6.500 -0.5554 0.03930 0.03222 -0.0231 1.0000 0.0293
-6.250 -0.5440 0.03652 0.02907 -0.0209 1.0000 0.0293
-6.000 -0.5307 0.03398 0.02616 -0.0187 1.0000 0.0293
-5.750 -0.5154 0.03170 0.02347 -0.0167 1.0000 0.0294
-5.500 -0.4982 0.02974 0.02113 -0.0148 1.0000 0.0298
-5.250 -0.4808 0.02772 0.01889 -0.0133 1.0000 0.0309
-5.000 -0.4618 0.02640 0.01746 -0.0119 1.0000 0.0323
-4.750 -0.4415 0.02507 0.01594 -0.0106 1.0000 0.0334
-4.500 -0.4200 0.02370 0.01438 -0.0093 1.0000 0.0339
-4.250 -0.3983 0.02248 0.01300 -0.0080 1.0000 0.0346
-4.000 -0.3765 0.02141 0.01182 -0.0068 1.0000 0.0354
-3.750 -0.3549 0.02047 0.01080 -0.0056 1.0000 0.0365
-3.500 -0.3337 0.01965 0.00991 -0.0044 1.0000 0.0379
-3.250 -0.3126 0.01898 0.00915 -0.0032 1.0000 0.0394
-3.000 -0.2825 0.01821 0.00840 -0.0040 0.9966 0.0437
-2.750 -0.2399 0.01754 0.00765 -0.0072 0.9880 0.0518
-2.500 -0.1957 0.01664 0.00680 -0.0106 0.9775 0.0723
-2.250 -0.1578 0.01501 0.00617 -0.0133 0.9669 0.2716
-2.000 -0.1268 0.01298 0.00634 -0.0132 0.9617 0.7550
-1.750 -0.0354 0.01331 0.00678 -0.0235 0.9689 0.9720
-1.500 0.0376 0.01326 0.00647 -0.0328 0.9681 0.9998
-1.250 0.0768 0.01313 0.00616 -0.0353 0.9539 1.0000
-1.000 0.1131 0.01300 0.00588 -0.0372 0.9377 1.0000
-0.750 0.1478 0.01286 0.00562 -0.0386 0.9194 1.0000
-0.500 0.1772 0.01274 0.00538 -0.0389 0.8966 1.0000
-0.250 0.2075 0.01260 0.00514 -0.0391 0.8725 1.0000
0.000 0.2371 0.01248 0.00489 -0.0392 0.8460 1.0000
0.250 0.2647 0.01239 0.00466 -0.0387 0.8161 1.0000
0.500 0.2908 0.01235 0.00446 -0.0379 0.7825 1.0000
0.750 0.3162 0.01236 0.00430 -0.0370 0.7462 1.0000
1.000 0.3406 0.01244 0.00419 -0.0359 0.7060 1.0000
1.250 0.3646 0.01257 0.00411 -0.0348 0.6627 1.0000
1.500 0.3882 0.01276 0.00406 -0.0337 0.6190 1.0000
1.750 0.4115 0.01300 0.00405 -0.0326 0.5786 1.0000
2.000 0.4347 0.01327 0.00412 -0.0316 0.5423 1.0000
2.250 0.4580 0.01355 0.00421 -0.0307 0.5104 1.0000
2.500 0.4814 0.01383 0.00433 -0.0298 0.4827 1.0000
2.750 0.5048 0.01413 0.00450 -0.0290 0.4590 1.0000
3.000 0.5283 0.01443 0.00469 -0.0282 0.4386 1.0000
3.250 0.5518 0.01474 0.00489 -0.0274 0.4211 1.0000
3.500 0.5754 0.01505 0.00513 -0.0266 0.4054 1.0000
3.750 0.5990 0.01537 0.00541 -0.0258 0.3911 1.0000
4.000 0.6228 0.01569 0.00570 -0.0251 0.3782 1.0000
4.250 0.6465 0.01602 0.00601 -0.0243 0.3662 1.0000
4.500 0.6701 0.01637 0.00634 -0.0236 0.3549 1.0000
4.750 0.6936 0.01675 0.00671 -0.0228 0.3446 1.0000
5.000 0.7173 0.01710 0.00711 -0.0221 0.3343 1.0000
5.250 0.7410 0.01748 0.00753 -0.0214 0.3246 1.0000
5.500 0.7644 0.01789 0.00793 -0.0206 0.3158 1.0000
5.750 0.7881 0.01827 0.00844 -0.0199 0.3063 1.0000
6.000 0.8116 0.01870 0.00892 -0.0192 0.2981 1.0000
6.250 0.8350 0.01913 0.00942 -0.0184 0.2895 1.0000
6.500 0.8585 0.01957 0.00997 -0.0177 0.2811 1.0000
6.750 0.8816 0.02003 0.01051 -0.0170 0.2732 1.0000
7.000 0.9042 0.02041 0.01105 -0.0161 0.2623 1.0000
7.250 0.9262 0.02077 0.01152 -0.0152 0.2501 1.0000
7.500 0.9478 0.02112 0.01199 -0.0142 0.2374 1.0000
7.750 0.9689 0.02146 0.01247 -0.0132 0.2228 1.0000
8.000 0.9892 0.02180 0.01290 -0.0121 0.2050 1.0000
8.250 1.0089 0.02225 0.01340 -0.0110 0.1865 1.0000
8.500 1.0290 0.02277 0.01405 -0.0100 0.1649 1.0000
8.750 1.0477 0.02345 0.01478 -0.0088 0.1363 1.0000
9.000 1.0622 0.02463 0.01579 -0.0073 0.0967 1.0000
9.250 1.0724 0.02632 0.01729 -0.0054 0.0706 1.0000
9.500 1.0814 0.02807 0.01900 -0.0032 0.0569 1.0000
9.750 1.0909 0.02965 0.02070 -0.0012 0.0481 1.0000
10.000 1.0986 0.03127 0.02244 0.0011 0.0424 1.0000
10.250 1.1045 0.03290 0.02419 0.0033 0.0380 1.0000
10.500 1.1057 0.03473 0.02613 0.0061 0.0354 1.0000
10.750 1.1069 0.03640 0.02799 0.0089 0.0332 1.0000
11.000 1.1068 0.03826 0.03000 0.0113 0.0312 1.0000
11.500 1.1002 0.04295 0.03492 0.0146 0.0280 1.0000
11.750 1.0963 0.04574 0.03783 0.0156 0.0268 1.0000
12.000 1.0951 0.04852 0.04082 0.0161 0.0258 1.0000
12.250 1.0931 0.05158 0.04406 0.0162 0.0250 1.0000
12.500 1.0905 0.05488 0.04754 0.0161 0.0243 1.0000
12.750 1.0874 0.05843 0.05126 0.0156 0.0236 1.0000
13.000 1.0833 0.06224 0.05524 0.0148 0.0231 1.0000
13.250 1.0781 0.06636 0.05952 0.0135 0.0226 1.0000
13.500 1.0717 0.07079 0.06411 0.0119 0.0221 1.0000
13.750 1.0641 0.07553 0.06900 0.0099 0.0217 1.0000
14.000 1.0556 0.08055 0.07417 0.0077 0.0213 1.0000
14.250 1.0460 0.08585 0.07960 0.0052 0.0210 1.0000
14.500 1.0353 0.09148 0.08536 0.0024 0.0207 1.0000
14.750 1.0235 0.09749 0.09152 -0.0006 0.0205 1.0000
15.000 1.0103 0.10400 0.09817 -0.0040 0.0204 1.0000
15.250 0.9947 0.11137 0.10571 -0.0080 0.0204 1.0000
15.500 0.9741 0.12042 0.11496 -0.0133 0.0206 1.0000
15.750 0.9206 0.13949 0.13436 -0.0245 0.0224 1.0000
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Polar data table (+)
Polar graphs
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