OAF128 AIRFOIL (oaf128-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: OAF128 AIRFOIL (oaf128-il) Reynolds number: 200,000 Max Cl/Cd: 56.54 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-oaf128-il-200000.txt Download as CSV file: xf-oaf128-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: OAF128 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.9756 0.09273 0.08858 0.0091 1.0000 0.0432
-13.250 -1.0120 0.08173 0.07740 0.0010 1.0000 0.0427
-13.000 -1.0457 0.07185 0.06730 -0.0070 1.0000 0.0424
-12.750 -1.0739 0.06359 0.05878 -0.0139 1.0000 0.0421
-12.500 -1.0970 0.05707 0.05199 -0.0191 1.0000 0.0420
-12.250 -1.1165 0.05232 0.04697 -0.0214 1.0000 0.0420
-12.000 -1.1250 0.04839 0.04272 -0.0222 1.0000 0.0421
-11.750 -1.1251 0.04492 0.03889 -0.0226 1.0000 0.0425
-11.500 -1.1193 0.04190 0.03545 -0.0228 1.0000 0.0430
-11.250 -1.1079 0.03915 0.03233 -0.0229 1.0000 0.0436
-11.000 -1.0885 0.03688 0.03006 -0.0229 1.0000 0.0445
-10.750 -1.0684 0.03509 0.02819 -0.0228 1.0000 0.0453
-10.500 -1.0475 0.03333 0.02630 -0.0228 1.0000 0.0462
-10.250 -1.0257 0.03161 0.02440 -0.0227 1.0000 0.0473
-10.000 -1.0029 0.02998 0.02254 -0.0227 1.0000 0.0484
-9.750 -0.9795 0.02834 0.02074 -0.0227 1.0000 0.0496
-9.500 -0.9553 0.02697 0.01946 -0.0227 1.0000 0.0512
-9.250 -0.9301 0.02584 0.01828 -0.0227 1.0000 0.0532
-9.000 -0.9041 0.02474 0.01701 -0.0228 1.0000 0.0553
-8.750 -0.8792 0.02335 0.01572 -0.0229 1.0000 0.0574
-8.500 -0.8527 0.02234 0.01470 -0.0230 1.0000 0.0602
-8.250 -0.8260 0.02125 0.01356 -0.0233 1.0000 0.0636
-8.000 -0.7986 0.02036 0.01271 -0.0236 1.0000 0.0681
-7.750 -0.7710 0.01937 0.01175 -0.0240 1.0000 0.0736
-7.500 -0.7427 0.01846 0.01086 -0.0244 1.0000 0.0815
-7.250 -0.7140 0.01762 0.01010 -0.0250 1.0000 0.0936
-7.000 -0.6848 0.01684 0.00935 -0.0255 1.0000 0.1117
-6.750 -0.6556 0.01610 0.00873 -0.0262 1.0000 0.1305
-6.500 -0.6258 0.01560 0.00826 -0.0268 1.0000 0.1480
-6.250 -0.5959 0.01522 0.00790 -0.0273 1.0000 0.1637
-6.000 -0.5658 0.01489 0.00758 -0.0278 1.0000 0.1786
-5.750 -0.5356 0.01452 0.00724 -0.0283 1.0000 0.1934
-5.500 -0.5054 0.01410 0.00688 -0.0289 1.0000 0.2088
-5.250 -0.4751 0.01369 0.00655 -0.0295 1.0000 0.2254
-5.000 -0.4445 0.01338 0.00630 -0.0301 1.0000 0.2445
-4.750 -0.4137 0.01310 0.00611 -0.0308 1.0000 0.2650
-4.500 -0.3828 0.01283 0.00595 -0.0314 1.0000 0.2844
-4.250 -0.3515 0.01257 0.00577 -0.0322 1.0000 0.3023
-4.000 -0.3198 0.01234 0.00561 -0.0330 1.0000 0.3202
-3.750 -0.2877 0.01212 0.00548 -0.0340 1.0000 0.3380
-3.500 -0.2511 0.01204 0.00547 -0.0359 0.9703 0.3569
-3.250 -0.2191 0.01213 0.00555 -0.0362 0.9264 0.3748
-3.000 -0.1962 0.01225 0.00561 -0.0344 0.8904 0.3905
-2.750 -0.1723 0.01232 0.00559 -0.0329 0.8587 0.4064
-2.500 -0.1472 0.01232 0.00556 -0.0318 0.8304 0.4217
-2.250 -0.1209 0.01231 0.00550 -0.0309 0.8033 0.4364
-2.000 -0.0938 0.01231 0.00543 -0.0302 0.7785 0.4514
-1.750 -0.0655 0.01230 0.00535 -0.0299 0.7540 0.4669
-1.500 -0.0370 0.01232 0.00530 -0.0296 0.7314 0.4836
-1.250 -0.0083 0.01234 0.00526 -0.0293 0.7098 0.5013
-1.000 0.0205 0.01233 0.00521 -0.0291 0.6887 0.5175
-0.750 0.0494 0.01231 0.00515 -0.0290 0.6681 0.5326
-0.500 0.0785 0.01230 0.00510 -0.0289 0.6484 0.5487
-0.250 0.1080 0.01228 0.00507 -0.0289 0.6308 0.5656
0.000 0.1376 0.01227 0.00507 -0.0289 0.6147 0.5833
0.250 0.1670 0.01226 0.00507 -0.0289 0.5993 0.6026
0.500 0.1962 0.01227 0.00509 -0.0289 0.5850 0.6243
0.750 0.2254 0.01228 0.00513 -0.0288 0.5713 0.6498
1.000 0.2544 0.01224 0.00521 -0.0287 0.5573 0.6780
1.250 0.2828 0.01223 0.00529 -0.0284 0.5441 0.7112
1.500 0.3100 0.01224 0.00536 -0.0278 0.5319 0.7487
1.750 0.3360 0.01216 0.00546 -0.0269 0.5190 0.7924
2.000 0.3594 0.01210 0.00551 -0.0252 0.5074 0.8437
2.250 0.3786 0.01192 0.00540 -0.0225 0.4963 0.9075
2.500 0.4079 0.01171 0.00522 -0.0224 0.4830 1.0000
2.750 0.4398 0.01192 0.00532 -0.0232 0.4704 1.0000
3.000 0.4709 0.01213 0.00539 -0.0238 0.4566 1.0000
3.250 0.5017 0.01227 0.00544 -0.0242 0.4400 1.0000
3.500 0.5323 0.01241 0.00551 -0.0247 0.4232 1.0000
3.750 0.5628 0.01257 0.00564 -0.0251 0.4078 1.0000
4.000 0.5932 0.01277 0.00578 -0.0255 0.3926 1.0000
4.250 0.6233 0.01298 0.00593 -0.0258 0.3777 1.0000
4.500 0.6532 0.01320 0.00609 -0.0261 0.3626 1.0000
4.750 0.6830 0.01344 0.00625 -0.0264 0.3474 1.0000
5.000 0.7126 0.01370 0.00644 -0.0267 0.3320 1.0000
5.250 0.7422 0.01395 0.00665 -0.0270 0.3159 1.0000
5.500 0.7716 0.01422 0.00689 -0.0273 0.2994 1.0000
5.750 0.8008 0.01452 0.00715 -0.0275 0.2823 1.0000
6.000 0.8299 0.01485 0.00743 -0.0278 0.2640 1.0000
6.250 0.8588 0.01521 0.00776 -0.0280 0.2437 1.0000
6.500 0.8871 0.01569 0.00816 -0.0283 0.2214 1.0000
6.750 0.9148 0.01632 0.00865 -0.0285 0.1986 1.0000
7.000 0.9427 0.01693 0.00920 -0.0287 0.1762 1.0000
7.250 0.9700 0.01762 0.00978 -0.0289 0.1590 1.0000
7.500 0.9969 0.01835 0.01044 -0.0290 0.1462 1.0000
7.750 1.0233 0.01915 0.01118 -0.0290 0.1364 1.0000
8.000 1.0488 0.02003 0.01196 -0.0290 0.1285 1.0000
8.250 1.0751 0.02076 0.01274 -0.0289 0.1219 1.0000
8.500 1.0999 0.02171 0.01360 -0.0288 0.1163 1.0000
8.750 1.1252 0.02257 0.01453 -0.0285 0.1115 1.0000
9.000 1.1501 0.02339 0.01536 -0.0283 0.1070 1.0000
9.250 1.1733 0.02466 0.01652 -0.0280 0.1030 1.0000
9.500 1.1979 0.02545 0.01747 -0.0277 0.0995 1.0000
9.750 1.2218 0.02635 0.01840 -0.0274 0.0961 1.0000
10.000 1.2445 0.02765 0.01959 -0.0270 0.0929 1.0000
10.250 1.2671 0.02874 0.02084 -0.0265 0.0902 1.0000
10.500 1.2893 0.02974 0.02197 -0.0261 0.0874 1.0000
10.750 1.3113 0.03077 0.02301 -0.0256 0.0847 1.0000
11.000 1.3329 0.03253 0.02467 -0.0252 0.0822 1.0000
11.250 1.3519 0.03362 0.02603 -0.0245 0.0802 1.0000
11.500 1.3705 0.03485 0.02742 -0.0238 0.0779 1.0000
11.750 1.3894 0.03603 0.02865 -0.0231 0.0758 1.0000
12.000 1.4098 0.03748 0.03003 -0.0226 0.0739 1.0000
12.250 1.4240 0.03941 0.03215 -0.0217 0.0722 1.0000
12.500 1.4346 0.04103 0.03404 -0.0205 0.0705 1.0000
12.750 1.4452 0.04264 0.03582 -0.0193 0.0688 1.0000
13.000 1.4561 0.04414 0.03741 -0.0182 0.0673 1.0000
13.250 1.4714 0.04564 0.03886 -0.0174 0.0659 1.0000
13.500 1.4780 0.04816 0.04149 -0.0162 0.0646 1.0000
13.750 1.4657 0.05059 0.04422 -0.0139 0.0639 1.0000
14.000 1.4540 0.05368 0.04758 -0.0130 0.0630 1.0000
14.250 1.4434 0.05719 0.05133 -0.0131 0.0622 1.0000
14.500 1.4339 0.06095 0.05530 -0.0139 0.0613 1.0000
14.750 1.4269 0.06468 0.05918 -0.0150 0.0605 1.0000
15.000 1.4186 0.06875 0.06340 -0.0165 0.0598 1.0000
15.250 1.4135 0.07256 0.06731 -0.0179 0.0590 1.0000
15.500 1.4253 0.07441 0.06907 -0.0173 0.0579 1.0000
15.750 1.4039 0.08078 0.07565 -0.0202 0.0575 1.0000
16.000 1.3698 0.08917 0.08433 -0.0253 0.0574 1.0000
16.250 1.3304 0.09907 0.09452 -0.0316 0.0574 1.0000
16.500 1.2832 0.11130 0.10702 -0.0398 0.0576 1.0000
16.750 0.7080 0.18958 0.18623 -0.0665 0.0824 1.0000
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