BELL/WORTMANN FX 69-H-098 AIRFOIL (fx69h098-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: BELL/WORTMANN FX 69-H-098 AIRFOIL (fx69h098-il) Reynolds number: 200,000 Max Cl/Cd: 59.66 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx69h098-il-200000.txt Download as CSV file: xf-fx69h098-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4082 0.09516 0.09180 -0.0170 1.0000 0.0518
-9.500 -0.4098 0.09105 0.08771 -0.0182 1.0000 0.0533
-9.250 -0.5384 0.09243 0.08899 -0.0174 1.0000 0.0482
-9.000 -0.5292 0.09027 0.08684 -0.0156 1.0000 0.0498
-8.750 -0.5278 0.08649 0.08308 -0.0174 1.0000 0.0510
-8.500 -0.5307 0.08192 0.07856 -0.0209 1.0000 0.0521
-8.250 -0.5391 0.07677 0.07342 -0.0254 1.0000 0.0529
-8.000 -0.5447 0.07174 0.06836 -0.0287 1.0000 0.0542
-7.750 -0.5505 0.06660 0.06308 -0.0314 1.0000 0.0564
-7.500 -0.5660 0.06421 0.06010 -0.0314 1.0000 0.0587
-7.250 -0.5709 0.05723 0.05307 -0.0305 1.0000 0.0599
-7.000 -0.5599 0.05370 0.04966 -0.0294 1.0000 0.0611
-6.750 -0.5508 0.05119 0.04715 -0.0278 1.0000 0.0627
-6.500 -0.5433 0.04870 0.04456 -0.0260 1.0000 0.0651
-6.250 -0.5399 0.04972 0.04479 -0.0218 1.0000 0.0721
-6.000 -0.5357 0.04270 0.03791 -0.0209 1.0000 0.0743
-5.750 -0.5230 0.04029 0.03554 -0.0193 1.0000 0.0765
-5.500 -0.5109 0.03832 0.03343 -0.0172 1.0000 0.0808
-5.250 -0.5022 0.03587 0.03064 -0.0147 1.0000 0.0889
-5.000 -0.4870 0.03413 0.02891 -0.0131 1.0000 0.0941
-4.750 -0.4646 0.02667 0.01977 -0.0074 1.0000 0.0474
-4.500 -0.4440 0.02395 0.01693 -0.0061 1.0000 0.0440
-4.250 -0.4225 0.02175 0.01441 -0.0046 1.0000 0.0420
-4.000 -0.3995 0.02007 0.01246 -0.0032 1.0000 0.0410
-3.750 -0.3762 0.01879 0.01100 -0.0021 1.0000 0.0410
-3.500 -0.3527 0.01777 0.00988 -0.0012 1.0000 0.0416
-3.250 -0.3295 0.01711 0.00915 -0.0003 1.0000 0.0437
-3.000 -0.2871 0.01630 0.00825 -0.0032 0.9955 0.0461
-2.750 -0.2477 0.01501 0.00700 -0.0056 0.9908 0.0490
-2.500 -0.2058 0.01427 0.00628 -0.0085 0.9852 0.0558
-2.250 -0.1667 0.01331 0.00544 -0.0109 0.9788 0.0889
-2.000 -0.1421 0.01047 0.00508 -0.0113 0.9736 0.6265
-1.750 -0.0860 0.01012 0.00567 -0.0146 0.9761 0.9411
-1.500 0.0093 0.01044 0.00577 -0.0276 0.9867 1.0000
-1.250 0.0590 0.01032 0.00551 -0.0323 0.9792 1.0000
-1.000 0.1104 0.01016 0.00523 -0.0373 0.9718 1.0000
-0.750 0.1552 0.00996 0.00495 -0.0408 0.9600 1.0000
-0.500 0.1954 0.00975 0.00466 -0.0432 0.9450 1.0000
-0.250 0.2292 0.00953 0.00438 -0.0441 0.9262 1.0000
0.000 0.2550 0.00934 0.00412 -0.0433 0.9004 1.0000
0.250 0.2793 0.00917 0.00386 -0.0420 0.8722 1.0000
0.500 0.3030 0.00904 0.00360 -0.0406 0.8408 1.0000
0.750 0.3265 0.00899 0.00341 -0.0392 0.8048 1.0000
1.000 0.3501 0.00904 0.00325 -0.0378 0.7657 1.0000
1.250 0.3736 0.00916 0.00316 -0.0366 0.7219 1.0000
1.500 0.3969 0.00933 0.00310 -0.0354 0.6720 1.0000
1.750 0.4199 0.00959 0.00307 -0.0343 0.6188 1.0000
2.000 0.4428 0.00990 0.00311 -0.0332 0.5691 1.0000
2.250 0.4660 0.01024 0.00319 -0.0323 0.5282 1.0000
2.500 0.4896 0.01055 0.00330 -0.0315 0.4949 1.0000
2.750 0.5132 0.01087 0.00346 -0.0307 0.4683 1.0000
3.000 0.5371 0.01116 0.00362 -0.0300 0.4460 1.0000
3.250 0.5610 0.01147 0.00381 -0.0293 0.4281 1.0000
3.500 0.5850 0.01177 0.00401 -0.0286 0.4123 1.0000
3.750 0.6090 0.01208 0.00426 -0.0279 0.3976 1.0000
4.000 0.6331 0.01237 0.00450 -0.0273 0.3837 1.0000
4.250 0.6572 0.01267 0.00478 -0.0266 0.3711 1.0000
4.500 0.6813 0.01300 0.00507 -0.0259 0.3594 1.0000
4.750 0.7053 0.01335 0.00540 -0.0252 0.3484 1.0000
5.000 0.7292 0.01371 0.00571 -0.0246 0.3379 1.0000
5.250 0.7533 0.01401 0.00607 -0.0239 0.3274 1.0000
5.500 0.7774 0.01438 0.00645 -0.0232 0.3181 1.0000
5.750 0.8013 0.01476 0.00681 -0.0225 0.3090 1.0000
6.000 0.8252 0.01508 0.00723 -0.0218 0.2996 1.0000
6.250 0.8486 0.01542 0.00758 -0.0211 0.2899 1.0000
6.500 0.8717 0.01570 0.00785 -0.0202 0.2793 1.0000
6.750 0.8945 0.01590 0.00819 -0.0193 0.2682 1.0000
7.000 0.9170 0.01610 0.00845 -0.0184 0.2560 1.0000
7.250 0.9393 0.01628 0.00870 -0.0175 0.2434 1.0000
7.500 0.9616 0.01652 0.00900 -0.0166 0.2318 1.0000
7.750 0.9837 0.01675 0.00932 -0.0157 0.2191 1.0000
8.000 1.0057 0.01696 0.00963 -0.0147 0.2035 1.0000
8.250 1.0273 0.01722 0.00996 -0.0138 0.1835 1.0000
8.500 1.0477 0.01763 0.01035 -0.0127 0.1498 1.0000
9.000 1.0674 0.02118 0.01324 -0.0080 0.0547 1.0000
9.250 1.0800 0.02254 0.01468 -0.0058 0.0457 1.0000
9.500 1.0891 0.02412 0.01630 -0.0033 0.0403 1.0000
9.750 1.1016 0.02538 0.01766 -0.0012 0.0366 1.0000
10.000 1.1098 0.02697 0.01928 0.0012 0.0339 1.0000
10.250 1.1160 0.02899 0.02137 0.0039 0.0320 1.0000
10.500 1.1279 0.03027 0.02282 0.0059 0.0300 1.0000
10.750 1.1367 0.03163 0.02429 0.0082 0.0282 1.0000
11.000 1.1439 0.03322 0.02595 0.0105 0.0269 1.0000
11.250 1.1512 0.03525 0.02802 0.0125 0.0259 1.0000
11.500 1.1610 0.03865 0.03154 0.0140 0.0250 1.0000
11.750 1.1663 0.04101 0.03412 0.0161 0.0246 1.0000
12.000 1.1686 0.04326 0.03661 0.0182 0.0243 1.0000
12.250 1.1681 0.04583 0.03943 0.0201 0.0240 1.0000
12.500 1.1644 0.04863 0.04248 0.0217 0.0238 1.0000
12.750 1.1578 0.05171 0.04581 0.0228 0.0236 1.0000
13.000 1.1489 0.05515 0.04949 0.0233 0.0233 1.0000
13.250 1.1378 0.05905 0.05364 0.0230 0.0231 1.0000
13.500 1.1246 0.06352 0.05834 0.0218 0.0230 1.0000
13.750 1.1097 0.06858 0.06362 0.0198 0.0229 1.0000
14.000 1.0928 0.07436 0.06961 0.0169 0.0229 1.0000
14.250 1.0739 0.08089 0.07634 0.0132 0.0230 1.0000
14.500 1.0535 0.08810 0.08374 0.0088 0.0232 1.0000
14.750 1.0315 0.09601 0.09183 0.0039 0.0235 1.0000
15.000 1.0084 0.10454 0.10050 -0.0013 0.0239 1.0000
15.250 0.9847 0.11369 0.10978 -0.0067 0.0243 1.0000
15.500 0.9608 0.12321 0.11938 -0.0119 0.0247 1.0000
15.750 0.9453 0.13177 0.12807 -0.0173 0.0251 1.0000
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Polar data table (+)
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