OAF139 AIRFOIL (oaf139-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: OAF139 AIRFOIL (oaf139-il) Reynolds number: 1,000,000 Max Cl/Cd: 73.07 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-oaf139-il-1000000.txt Download as CSV file: xf-oaf139-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: OAF139 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -1.6424 0.08470 0.08057 0.0453 1.0000 0.0269
-18.000 -1.6675 0.07747 0.07322 0.0425 1.0000 0.0272
-17.750 -1.6906 0.07085 0.06649 0.0401 1.0000 0.0275
-17.500 -1.7119 0.06459 0.06011 0.0380 1.0000 0.0278
-17.250 -1.7296 0.05886 0.05428 0.0361 1.0000 0.0282
-17.000 -1.7434 0.05371 0.04901 0.0345 1.0000 0.0286
-16.750 -1.7533 0.04907 0.04426 0.0330 1.0000 0.0291
-16.500 -1.7593 0.04495 0.04004 0.0317 1.0000 0.0296
-16.250 -1.7611 0.04141 0.03639 0.0307 1.0000 0.0302
-16.000 -1.7591 0.03840 0.03328 0.0298 1.0000 0.0307
-15.750 -1.7636 0.03472 0.02950 0.0289 1.0000 0.0315
-15.500 -1.7629 0.03192 0.02663 0.0286 1.0000 0.0324
-15.250 -1.7596 0.02972 0.02436 0.0289 1.0000 0.0332
-15.000 -1.7552 0.02798 0.02255 0.0299 1.0000 0.0341
-14.750 -1.7496 0.02671 0.02119 0.0318 1.0000 0.0349
-14.500 -1.7422 0.02552 0.01993 0.0338 1.0000 0.0359
-14.250 -1.7303 0.02447 0.01886 0.0353 1.0000 0.0372
-14.000 -1.7140 0.02364 0.01799 0.0365 1.0000 0.0386
-13.750 -1.6947 0.02297 0.01727 0.0373 1.0000 0.0397
-13.500 -1.6763 0.02214 0.01640 0.0382 1.0000 0.0412
-13.250 -1.6565 0.02139 0.01564 0.0390 1.0000 0.0429
-13.000 -1.6346 0.02080 0.01502 0.0396 1.0000 0.0446
-12.750 -1.6118 0.02026 0.01443 0.0401 1.0000 0.0460
-12.500 -1.5900 0.01955 0.01373 0.0407 1.0000 0.0482
-12.250 -1.5664 0.01901 0.01317 0.0411 1.0000 0.0501
-12.000 -1.5415 0.01860 0.01272 0.0414 1.0000 0.0516
-11.750 -1.5180 0.01795 0.01207 0.0418 1.0000 0.0542
-11.500 -1.4931 0.01746 0.01158 0.0421 1.0000 0.0565
-11.250 -1.4672 0.01708 0.01117 0.0423 1.0000 0.0583
-11.000 -1.4421 0.01653 0.01061 0.0426 1.0000 0.0611
-10.750 -1.4162 0.01608 0.01017 0.0427 1.0000 0.0638
-10.500 -1.3894 0.01574 0.00980 0.0428 1.0000 0.0660
-10.250 -1.3633 0.01523 0.00931 0.0430 1.0000 0.0695
-10.000 -1.3365 0.01483 0.00892 0.0431 1.0000 0.0726
-9.750 -1.3092 0.01450 0.00856 0.0431 1.0000 0.0754
-9.500 -1.2823 0.01404 0.00813 0.0432 1.0000 0.0799
-9.250 -1.2546 0.01371 0.00780 0.0432 1.0000 0.0834
-9.000 -1.2271 0.01329 0.00741 0.0432 1.0000 0.0886
-8.750 -1.1992 0.01295 0.00708 0.0431 1.0000 0.0934
-8.500 -1.1714 0.01255 0.00672 0.0431 1.0000 0.1000
-8.250 -1.1431 0.01222 0.00641 0.0430 1.0000 0.1065
-8.000 -1.1150 0.01183 0.00608 0.0429 1.0000 0.1155
-7.750 -1.0866 0.01144 0.00576 0.0428 1.0000 0.1261
-7.500 -1.0581 0.01108 0.00547 0.0427 1.0000 0.1378
-7.250 -1.0294 0.01073 0.00520 0.0425 1.0000 0.1506
-7.000 -1.0005 0.01042 0.00495 0.0423 1.0000 0.1631
-6.750 -0.9714 0.01016 0.00474 0.0421 1.0000 0.1745
-6.500 -0.9421 0.00991 0.00455 0.0420 1.0000 0.1854
-6.250 -0.9128 0.00965 0.00435 0.0418 1.0000 0.1955
-6.000 -0.8832 0.00946 0.00417 0.0416 1.0000 0.2042
-5.750 -0.8536 0.00922 0.00400 0.0413 1.0000 0.2142
-5.500 -0.8239 0.00900 0.00383 0.0411 1.0000 0.2237
-5.250 -0.7941 0.00881 0.00368 0.0409 1.0000 0.2335
-5.000 -0.7720 0.00898 0.00369 0.0426 0.8605 0.2444
-4.750 -0.7445 0.00899 0.00354 0.0429 0.7911 0.2560
-4.500 -0.7154 0.00897 0.00340 0.0429 0.7384 0.2676
-4.250 -0.6857 0.00892 0.00326 0.0427 0.6940 0.2799
-4.000 -0.6559 0.00886 0.00313 0.0425 0.6574 0.2909
-3.750 -0.6260 0.00882 0.00302 0.0423 0.6285 0.3007
-3.500 -0.5960 0.00875 0.00292 0.0420 0.5999 0.3121
-3.250 -0.5660 0.00870 0.00282 0.0418 0.5742 0.3224
-3.000 -0.5359 0.00866 0.00274 0.0416 0.5519 0.3327
-2.750 -0.5059 0.00858 0.00266 0.0413 0.5344 0.3443
-2.500 -0.4758 0.00853 0.00259 0.0411 0.5183 0.3555
-2.250 -0.4456 0.00849 0.00253 0.0409 0.5025 0.3667
-2.000 -0.4155 0.00842 0.00247 0.0406 0.4882 0.3769
-1.500 -0.3551 0.00835 0.00238 0.0402 0.4634 0.3962
-1.250 -0.3249 0.00833 0.00234 0.0400 0.4518 0.4052
-1.000 -0.2947 0.00828 0.00231 0.0398 0.4403 0.4156
-0.500 -0.2342 0.00824 0.00226 0.0393 0.4173 0.4345
-0.250 -0.2039 0.00823 0.00225 0.0391 0.4059 0.4441
0.000 -0.1736 0.00823 0.00223 0.0389 0.3934 0.4544
0.250 -0.1433 0.00821 0.00222 0.0386 0.3815 0.4638
0.500 -0.1130 0.00822 0.00222 0.0384 0.3696 0.4737
0.750 -0.0827 0.00821 0.00223 0.0382 0.3578 0.4845
1.250 -0.0220 0.00824 0.00225 0.0377 0.3346 0.5059
1.500 0.0083 0.00826 0.00227 0.0375 0.3223 0.5164
1.750 0.0386 0.00828 0.00231 0.0372 0.3106 0.5290
2.000 0.0689 0.00831 0.00234 0.0370 0.2977 0.5423
2.500 0.1296 0.00838 0.00244 0.0365 0.2716 0.5707
2.750 0.1600 0.00843 0.00250 0.0362 0.2587 0.5856
3.000 0.1903 0.00849 0.00257 0.0359 0.2460 0.5996
3.500 0.2509 0.00863 0.00272 0.0354 0.2223 0.6291
3.750 0.2812 0.00870 0.00282 0.0351 0.2117 0.6465
4.250 0.3417 0.00884 0.00303 0.0346 0.1914 0.6848
4.500 0.3718 0.00893 0.00316 0.0343 0.1813 0.7054
4.750 0.4019 0.00903 0.00329 0.0341 0.1700 0.7277
5.000 0.4319 0.00911 0.00342 0.0339 0.1595 0.7518
5.250 0.4617 0.00921 0.00357 0.0337 0.1483 0.7779
5.500 0.4912 0.00933 0.00374 0.0336 0.1378 0.8075
5.750 0.5202 0.00945 0.00392 0.0336 0.1285 0.8396
6.000 0.5485 0.00952 0.00410 0.0338 0.1212 0.8736
6.250 0.5754 0.00965 0.00429 0.0343 0.1133 0.9092
6.500 0.5998 0.00963 0.00437 0.0355 0.1082 0.9559
6.750 0.6308 0.00980 0.00452 0.0350 0.1012 1.0000
7.000 0.6611 0.01001 0.00471 0.0346 0.0960 1.0000
7.250 0.6913 0.01030 0.00495 0.0342 0.0900 1.0000
7.500 0.7214 0.01053 0.00517 0.0339 0.0851 1.0000
7.750 0.7514 0.01082 0.00543 0.0335 0.0798 1.0000
8.000 0.7813 0.01110 0.00568 0.0332 0.0749 1.0000
8.250 0.8111 0.01140 0.00596 0.0328 0.0703 1.0000
8.500 0.8407 0.01172 0.00626 0.0325 0.0658 1.0000
8.750 0.8703 0.01203 0.00656 0.0322 0.0617 1.0000
9.000 0.8997 0.01242 0.00692 0.0318 0.0574 1.0000
9.250 0.9291 0.01273 0.00724 0.0316 0.0542 1.0000
9.500 0.9581 0.01317 0.00765 0.0312 0.0507 1.0000
9.750 0.9872 0.01351 0.00801 0.0310 0.0480 1.0000
10.000 1.0159 0.01396 0.00844 0.0306 0.0452 1.0000
10.250 1.0446 0.01436 0.00887 0.0304 0.0430 1.0000
10.500 1.0731 0.01479 0.00931 0.0301 0.0409 1.0000
10.750 1.1011 0.01538 0.00989 0.0298 0.0388 1.0000
11.000 1.1293 0.01576 0.01032 0.0296 0.0375 1.0000
11.250 1.1570 0.01626 0.01082 0.0294 0.0359 1.0000
11.500 1.1839 0.01699 0.01156 0.0291 0.0341 1.0000
11.750 1.2115 0.01740 0.01202 0.0289 0.0332 1.0000
12.000 1.2385 0.01792 0.01257 0.0288 0.0320 1.0000
12.250 1.2647 0.01858 0.01325 0.0286 0.0309 1.0000
12.500 1.2897 0.01948 0.01419 0.0283 0.0298 1.0000
12.750 1.3158 0.02003 0.01480 0.0282 0.0291 1.0000
13.000 1.3411 0.02067 0.01549 0.0281 0.0284 1.0000
13.250 1.3656 0.02141 0.01627 0.0280 0.0276 1.0000
13.500 1.3888 0.02231 0.01721 0.0278 0.0269 1.0000
13.750 1.4086 0.02369 0.01865 0.0275 0.0260 1.0000
14.000 1.4308 0.02454 0.01958 0.0275 0.0256 1.0000
14.250 1.4521 0.02548 0.02059 0.0274 0.0251 1.0000
14.500 1.4716 0.02656 0.02174 0.0272 0.0245 1.0000
14.750 1.4889 0.02786 0.02311 0.0269 0.0240 1.0000
15.000 1.5022 0.02958 0.02491 0.0263 0.0236 1.0000
15.250 1.5017 0.03341 0.02889 0.0226 0.0233 1.0000
15.500 1.4923 0.03936 0.03499 0.0170 0.0231 1.0000
15.750 1.4760 0.04595 0.04173 0.0121 0.0230 1.0000
16.000 1.4529 0.05307 0.04899 0.0077 0.0229 1.0000
16.250 1.4253 0.06061 0.05667 0.0034 0.0228 1.0000
16.500 1.3964 0.06825 0.06444 -0.0008 0.0228 1.0000
16.750 1.3674 0.07594 0.07225 -0.0048 0.0227 1.0000
17.000 1.3395 0.08366 0.08009 -0.0089 0.0227 1.0000
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Polar data table (+)
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