OAF128 AIRFOIL (oaf128-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: OAF128 AIRFOIL (oaf128-il) Reynolds number: 100,000 Max Cl/Cd: 43.54 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oaf128-il-100000-n5.txt Download as CSV file: xf-oaf128-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.9210 0.09403 0.08826 0.0125 1.0000 0.0410
-12.750 -0.9909 0.07598 0.06976 -0.0013 1.0000 0.0401
-12.500 -1.0155 0.06763 0.06116 -0.0077 1.0000 0.0401
-12.250 -1.0303 0.06134 0.05464 -0.0126 1.0000 0.0403
-12.000 -1.0405 0.05616 0.04925 -0.0164 1.0000 0.0407
-11.750 -1.0482 0.05187 0.04473 -0.0191 1.0000 0.0411
-11.500 -1.0525 0.04842 0.04105 -0.0204 1.0000 0.0417
-11.250 -1.0488 0.04541 0.03776 -0.0210 1.0000 0.0424
-11.000 -1.0404 0.04268 0.03473 -0.0214 1.0000 0.0432
-10.750 -1.0264 0.04062 0.03259 -0.0214 1.0000 0.0440
-10.500 -1.0103 0.03882 0.03076 -0.0214 1.0000 0.0450
-10.250 -0.9930 0.03707 0.02888 -0.0216 1.0000 0.0463
-10.000 -0.9745 0.03530 0.02693 -0.0217 1.0000 0.0481
-9.750 -0.9546 0.03366 0.02517 -0.0218 1.0000 0.0499
-9.500 -0.9336 0.03224 0.02372 -0.0220 1.0000 0.0517
-9.250 -0.9114 0.03081 0.02218 -0.0221 1.0000 0.0539
-9.000 -0.8885 0.02942 0.02069 -0.0223 1.0000 0.0563
-8.750 -0.8647 0.02819 0.01945 -0.0226 1.0000 0.0594
-8.500 -0.8400 0.02698 0.01815 -0.0229 1.0000 0.0634
-8.250 -0.8146 0.02586 0.01700 -0.0233 1.0000 0.0680
-8.000 -0.7886 0.02476 0.01589 -0.0238 1.0000 0.0737
-7.750 -0.7619 0.02375 0.01485 -0.0243 1.0000 0.0816
-7.500 -0.7346 0.02281 0.01391 -0.0248 1.0000 0.0915
-7.250 -0.7068 0.02194 0.01305 -0.0253 1.0000 0.1037
-7.000 -0.6786 0.02116 0.01225 -0.0259 1.0000 0.1171
-6.750 -0.6501 0.02046 0.01156 -0.0264 1.0000 0.1314
-6.500 -0.6212 0.01985 0.01098 -0.0270 1.0000 0.1460
-6.250 -0.5920 0.01932 0.01046 -0.0275 1.0000 0.1613
-6.000 -0.5626 0.01885 0.00998 -0.0281 1.0000 0.1777
-5.750 -0.5330 0.01840 0.00951 -0.0286 1.0000 0.1952
-5.500 -0.5034 0.01792 0.00907 -0.0292 1.0000 0.2127
-5.250 -0.4737 0.01747 0.00870 -0.0298 1.0000 0.2290
-5.000 -0.4438 0.01707 0.00836 -0.0303 1.0000 0.2449
-4.750 -0.4137 0.01671 0.00804 -0.0308 1.0000 0.2611
-4.500 -0.3835 0.01637 0.00777 -0.0314 1.0000 0.2772
-4.250 -0.3532 0.01607 0.00752 -0.0320 1.0000 0.2936
-4.000 -0.3227 0.01579 0.00731 -0.0327 1.0000 0.3100
-3.750 -0.2897 0.01562 0.00717 -0.0338 0.9734 0.3275
-3.500 -0.2534 0.01555 0.00710 -0.0353 0.9288 0.3455
-3.250 -0.2238 0.01553 0.00705 -0.0352 0.8930 0.3620
-3.000 -0.1972 0.01552 0.00699 -0.0344 0.8615 0.3777
-2.750 -0.1713 0.01551 0.00693 -0.0334 0.8330 0.3935
-2.500 -0.1449 0.01549 0.00685 -0.0326 0.8059 0.4099
-2.250 -0.1183 0.01547 0.00676 -0.0318 0.7811 0.4271
-2.000 -0.0910 0.01545 0.00668 -0.0312 0.7570 0.4444
-1.750 -0.0633 0.01541 0.00660 -0.0307 0.7344 0.4601
-1.500 -0.0355 0.01536 0.00652 -0.0303 0.7131 0.4744
-1.250 -0.0074 0.01532 0.00644 -0.0299 0.6930 0.4889
-1.000 0.0210 0.01530 0.00636 -0.0296 0.6742 0.5036
-0.750 0.0495 0.01529 0.00630 -0.0293 0.6565 0.5190
-0.500 0.0779 0.01528 0.00628 -0.0291 0.6398 0.5348
-0.250 0.1064 0.01527 0.00626 -0.0288 0.6235 0.5516
0.000 0.1348 0.01527 0.00624 -0.0285 0.6068 0.5700
0.250 0.1631 0.01528 0.00624 -0.0282 0.5897 0.5907
0.500 0.1915 0.01528 0.00627 -0.0280 0.5729 0.6146
0.750 0.2196 0.01527 0.00632 -0.0276 0.5578 0.6399
1.000 0.2476 0.01528 0.00639 -0.0272 0.5444 0.6677
1.250 0.2749 0.01530 0.00644 -0.0266 0.5320 0.6970
1.500 0.3022 0.01530 0.00654 -0.0261 0.5184 0.7298
1.750 0.3282 0.01530 0.00662 -0.0252 0.5062 0.7665
2.250 0.3764 0.01522 0.00671 -0.0223 0.4825 0.8557
2.500 0.4009 0.01510 0.00665 -0.0210 0.4709 0.9203
2.750 0.4330 0.01513 0.00661 -0.0216 0.4585 1.0000
3.000 0.4641 0.01535 0.00679 -0.0223 0.4453 1.0000
3.250 0.4946 0.01560 0.00696 -0.0228 0.4326 1.0000
3.500 0.5247 0.01585 0.00711 -0.0231 0.4202 1.0000
3.750 0.5548 0.01609 0.00732 -0.0235 0.4053 1.0000
4.000 0.5847 0.01633 0.00749 -0.0239 0.3882 1.0000
4.250 0.6142 0.01657 0.00767 -0.0242 0.3703 1.0000
4.500 0.6437 0.01684 0.00788 -0.0244 0.3530 1.0000
4.750 0.6731 0.01713 0.00813 -0.0247 0.3364 1.0000
5.000 0.7023 0.01744 0.00841 -0.0250 0.3200 1.0000
5.250 0.7313 0.01778 0.00871 -0.0252 0.3035 1.0000
5.500 0.7601 0.01815 0.00904 -0.0255 0.2868 1.0000
5.750 0.7887 0.01854 0.00941 -0.0257 0.2697 1.0000
6.000 0.8169 0.01898 0.00980 -0.0259 0.2522 1.0000
6.250 0.8449 0.01948 0.01024 -0.0261 0.2348 1.0000
6.500 0.8723 0.02004 0.01075 -0.0263 0.2173 1.0000
6.750 0.8995 0.02066 0.01131 -0.0265 0.2001 1.0000
7.000 0.9265 0.02130 0.01194 -0.0266 0.1829 1.0000
7.250 0.9530 0.02200 0.01262 -0.0267 0.1671 1.0000
7.500 0.9788 0.02277 0.01333 -0.0268 0.1537 1.0000
7.750 1.0042 0.02358 0.01412 -0.0268 0.1424 1.0000
8.000 1.0293 0.02442 0.01498 -0.0267 0.1332 1.0000
8.250 1.0533 0.02536 0.01588 -0.0266 0.1259 1.0000
8.500 1.0773 0.02627 0.01684 -0.0265 0.1192 1.0000
8.750 1.0999 0.02732 0.01785 -0.0262 0.1141 1.0000
9.000 1.1229 0.02829 0.01892 -0.0259 0.1089 1.0000
9.250 1.1444 0.02937 0.01998 -0.0256 0.1047 1.0000
9.500 1.1657 0.03050 0.02118 -0.0251 0.1009 1.0000
9.750 1.1867 0.03162 0.02240 -0.0246 0.0971 1.0000
10.000 1.2063 0.03279 0.02359 -0.0241 0.0939 1.0000
10.250 1.2252 0.03409 0.02494 -0.0235 0.0911 1.0000
10.500 1.2438 0.03539 0.02641 -0.0229 0.0881 1.0000
10.750 1.2610 0.03672 0.02781 -0.0222 0.0854 1.0000
11.000 1.2774 0.03807 0.02915 -0.0215 0.0832 1.0000
11.250 1.2922 0.03964 0.03085 -0.0207 0.0810 1.0000
11.500 1.3048 0.04131 0.03274 -0.0198 0.0788 1.0000
11.750 1.3158 0.04298 0.03454 -0.0188 0.0767 1.0000
12.000 1.3255 0.04462 0.03624 -0.0178 0.0750 1.0000
12.250 1.3347 0.04623 0.03784 -0.0167 0.0735 1.0000
12.500 1.3359 0.04852 0.04034 -0.0156 0.0722 1.0000
12.750 1.3342 0.05128 0.04337 -0.0151 0.0708 1.0000
13.000 1.3324 0.05426 0.04655 -0.0152 0.0694 1.0000
13.250 1.3307 0.05737 0.04984 -0.0157 0.0681 1.0000
13.500 1.3299 0.06047 0.05306 -0.0164 0.0670 1.0000
14.000 1.3363 0.06597 0.05862 -0.0172 0.0649 1.0000
14.250 1.3182 0.07180 0.06478 -0.0200 0.0642 1.0000
14.500 1.2966 0.07848 0.07178 -0.0236 0.0635 1.0000
14.750 1.2700 0.08636 0.07995 -0.0282 0.0630 1.0000
15.000 1.2334 0.09644 0.09033 -0.0345 0.0627 1.0000
15.250 1.1503 0.11697 0.11130 -0.0483 0.0631 1.0000
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