RAF 38 AIRFOIL (raf38-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 38 AIRFOIL (raf38-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.68 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf38-il-1000000.txt Download as CSV file: xf-raf38-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 38 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
------ -------- --------- --------- -------- -------- --------
-17.250 -0.9501 0.09311 0.09065 -0.0379 1.0000 0.0134
-17.000 -1.0062 0.07984 0.07721 -0.0457 1.0000 0.0132
-16.750 -1.0632 0.06642 0.06355 -0.0539 1.0000 0.0128
-16.500 -1.0981 0.05648 0.05344 -0.0607 1.0000 0.0129
-16.250 -1.1211 0.04880 0.04559 -0.0663 1.0000 0.0129
-16.000 -1.1395 0.04233 0.03894 -0.0711 1.0000 0.0129
-15.750 -1.1475 0.03809 0.03456 -0.0737 1.0000 0.0130
-15.500 -1.1502 0.03503 0.03140 -0.0750 1.0000 0.0132
-15.250 -1.1562 0.03212 0.02836 -0.0754 1.0000 0.0133
-15.000 -1.1527 0.03041 0.02656 -0.0749 1.0000 0.0136
-14.750 -1.1534 0.02860 0.02464 -0.0737 1.0000 0.0137
-14.500 -1.1510 0.02723 0.02316 -0.0719 1.0000 0.0139
-14.250 -1.1482 0.02603 0.02186 -0.0696 1.0000 0.0141
-14.000 -1.1429 0.02511 0.02085 -0.0670 1.0000 0.0143
-13.750 -1.1401 0.02423 0.01987 -0.0637 1.0000 0.0144
-13.500 -1.1325 0.02359 0.01916 -0.0608 1.0000 0.0146
-13.250 -1.1318 0.02227 0.01774 -0.0572 1.0000 0.0150
-13.000 -1.1238 0.02133 0.01674 -0.0545 1.0000 0.0154
-12.750 -1.1120 0.02061 0.01597 -0.0522 1.0000 0.0158
-12.500 -1.0975 0.02006 0.01536 -0.0502 1.0000 0.0162
-12.250 -1.0833 0.01948 0.01472 -0.0480 1.0000 0.0166
-12.000 -1.0688 0.01892 0.01410 -0.0459 1.0000 0.0170
-11.750 -1.0542 0.01836 0.01348 -0.0437 1.0000 0.0174
-11.500 -1.0379 0.01795 0.01301 -0.0418 1.0000 0.0178
-11.250 -1.0280 0.01712 0.01210 -0.0389 1.0000 0.0184
-11.000 -1.0005 0.01642 0.01137 -0.0394 0.9987 0.0192
-10.750 -0.9669 0.01589 0.01080 -0.0410 0.9964 0.0200
-10.500 -0.9327 0.01540 0.01026 -0.0427 0.9939 0.0209
-10.250 -0.9011 0.01494 0.00973 -0.0438 0.9903 0.0216
-10.000 -0.8696 0.01422 0.00900 -0.0450 0.9862 0.0231
-9.750 -0.8344 0.01380 0.00856 -0.0468 0.9830 0.0243
-9.500 -0.8045 0.01343 0.00815 -0.0474 0.9758 0.0254
-9.250 -0.7695 0.01285 0.00754 -0.0492 0.9708 0.0271
-9.000 -0.7344 0.01252 0.00722 -0.0509 0.9624 0.0288
-8.750 -0.6946 0.01226 0.00691 -0.0535 0.9532 0.0304
-8.500 -0.6579 0.01181 0.00645 -0.0557 0.9363 0.0327
-8.250 -0.6244 0.01166 0.00624 -0.0568 0.9112 0.0346
-8.000 -0.5971 0.01159 0.00604 -0.0566 0.8848 0.0359
-7.750 -0.5743 0.01130 0.00566 -0.0556 0.8625 0.0379
-7.500 -0.5493 0.01124 0.00554 -0.0550 0.8455 0.0396
-7.250 -0.5238 0.01118 0.00541 -0.0544 0.8312 0.0412
-7.000 -0.4979 0.01112 0.00529 -0.0540 0.8191 0.0424
-6.750 -0.4745 0.01081 0.00490 -0.0531 0.8084 0.0443
-6.500 -0.4496 0.01063 0.00469 -0.0525 0.7981 0.0461
-6.250 -0.4239 0.01050 0.00452 -0.0520 0.7881 0.0477
-5.750 -0.3720 0.01030 0.00421 -0.0511 0.7683 0.0503
-5.500 -0.3472 0.01008 0.00391 -0.0504 0.7595 0.0517
-5.250 -0.3227 0.00975 0.00356 -0.0497 0.7511 0.0541
-5.000 -0.2970 0.00960 0.00337 -0.0492 0.7439 0.0559
-4.750 -0.2707 0.00944 0.00319 -0.0489 0.7369 0.0576
-4.500 -0.2445 0.00932 0.00302 -0.0484 0.7301 0.0591
-4.250 -0.2178 0.00920 0.00287 -0.0481 0.7238 0.0601
-4.000 -0.1920 0.00899 0.00262 -0.0476 0.7171 0.0626
-3.750 -0.1661 0.00882 0.00242 -0.0472 0.7113 0.0654
-3.500 -0.1394 0.00867 0.00226 -0.0468 0.7053 0.0680
-3.250 -0.1128 0.00857 0.00213 -0.0465 0.6993 0.0704
-3.000 -0.0862 0.00844 0.00198 -0.0461 0.6935 0.0746
-2.750 -0.0598 0.00826 0.00184 -0.0458 0.6875 0.0833
-2.500 -0.0363 0.00785 0.00168 -0.0450 0.6818 0.1501
-2.250 -0.0108 0.00761 0.00160 -0.0445 0.6766 0.1964
-2.000 0.0154 0.00744 0.00152 -0.0442 0.6709 0.2256
-1.750 0.0409 0.00726 0.00144 -0.0437 0.6652 0.2632
-1.500 0.0655 0.00695 0.00137 -0.0431 0.6597 0.3334
-1.250 0.0901 0.00667 0.00132 -0.0424 0.6538 0.4064
-1.000 0.1148 0.00648 0.00129 -0.0418 0.6482 0.4674
-0.750 0.1404 0.00629 0.00127 -0.0413 0.6429 0.5169
-0.500 0.1653 0.00612 0.00125 -0.0406 0.6370 0.5700
-0.250 0.1890 0.00594 0.00124 -0.0397 0.6311 0.6333
0.000 0.2134 0.00576 0.00125 -0.0388 0.6250 0.6914
0.250 0.2379 0.00566 0.00126 -0.0380 0.6187 0.7364
0.500 0.2630 0.00558 0.00129 -0.0372 0.6127 0.7740
0.750 0.2876 0.00548 0.00131 -0.0363 0.6050 0.8150
1.000 0.3125 0.00541 0.00134 -0.0355 0.5964 0.8558
1.250 0.3397 0.00538 0.00139 -0.0351 0.5864 0.8912
1.500 0.3722 0.00541 0.00147 -0.0359 0.5759 0.9246
1.750 0.4108 0.00552 0.00157 -0.0381 0.5640 0.9456
2.250 0.4816 0.00577 0.00172 -0.0412 0.5360 0.9639
2.500 0.5146 0.00592 0.00180 -0.0422 0.5178 0.9709
2.750 0.5534 0.00608 0.00190 -0.0445 0.5022 0.9742
3.000 0.5898 0.00625 0.00201 -0.0464 0.4874 0.9789
3.250 0.6226 0.00643 0.00213 -0.0474 0.4721 0.9833
3.500 0.6594 0.00660 0.00222 -0.0494 0.4528 0.9853
3.750 0.6950 0.00676 0.00232 -0.0512 0.4390 0.9877
4.000 0.7294 0.00693 0.00244 -0.0527 0.4262 0.9905
4.500 0.7983 0.00724 0.00266 -0.0558 0.3981 0.9952
4.750 0.8344 0.00740 0.00276 -0.0577 0.3818 0.9974
5.000 0.8716 0.00760 0.00288 -0.0599 0.3590 0.9996
5.250 0.8957 0.00782 0.00302 -0.0593 0.3355 1.0000
5.500 0.9138 0.00816 0.00320 -0.0576 0.3006 1.0000
5.750 0.9293 0.00866 0.00347 -0.0553 0.2565 1.0000
6.000 0.9453 0.00912 0.00377 -0.0532 0.2223 1.0000
6.250 0.9616 0.00957 0.00407 -0.0511 0.1927 1.0000
6.500 0.9765 0.01010 0.00441 -0.0487 0.1575 1.0000
6.750 0.9857 0.01093 0.00493 -0.0455 0.1027 1.0000
7.000 0.9993 0.01150 0.00535 -0.0429 0.0792 1.0000
7.250 1.0170 0.01185 0.00568 -0.0411 0.0714 1.0000
7.500 1.0342 0.01223 0.00602 -0.0391 0.0656 1.0000
7.750 1.0531 0.01250 0.00631 -0.0375 0.0626 1.0000
8.000 1.0717 0.01280 0.00661 -0.0358 0.0599 1.0000
8.250 1.0888 0.01316 0.00697 -0.0339 0.0566 1.0000
8.500 1.1057 0.01353 0.00735 -0.0320 0.0536 1.0000
8.750 1.1250 0.01378 0.00762 -0.0305 0.0517 1.0000
9.000 1.1426 0.01410 0.00795 -0.0287 0.0492 1.0000
9.250 1.1576 0.01454 0.00837 -0.0265 0.0460 1.0000
9.500 1.1749 0.01485 0.00872 -0.0248 0.0440 1.0000
9.750 1.1897 0.01515 0.00903 -0.0225 0.0416 1.0000
10.000 1.2009 0.01557 0.00943 -0.0197 0.0389 1.0000
10.250 1.2142 0.01596 0.00985 -0.0173 0.0365 1.0000
10.500 1.2278 0.01639 0.01028 -0.0151 0.0340 1.0000
10.750 1.2392 0.01697 0.01085 -0.0127 0.0314 1.0000
11.000 1.2535 0.01745 0.01137 -0.0108 0.0295 1.0000
11.250 1.2655 0.01810 0.01201 -0.0088 0.0278 1.0000
11.500 1.2760 0.01887 0.01282 -0.0067 0.0260 1.0000
11.750 1.2892 0.01954 0.01354 -0.0051 0.0248 1.0000
12.000 1.3009 0.02035 0.01437 -0.0035 0.0237 1.0000
12.250 1.3099 0.02139 0.01544 -0.0018 0.0224 1.0000
12.500 1.3190 0.02249 0.01659 -0.0003 0.0215 1.0000
12.750 1.3303 0.02350 0.01767 0.0009 0.0208 1.0000
13.000 1.3422 0.02450 0.01870 0.0019 0.0198 1.0000
13.250 1.3502 0.02584 0.02009 0.0030 0.0191 1.0000
13.500 1.3557 0.02745 0.02174 0.0042 0.0184 1.0000
13.750 1.3611 0.02912 0.02348 0.0052 0.0177 1.0000
14.000 1.3693 0.03061 0.02504 0.0059 0.0174 1.0000
14.250 1.3773 0.03215 0.02664 0.0066 0.0169 1.0000
14.500 1.3835 0.03387 0.02843 0.0073 0.0165 1.0000
14.750 1.3901 0.03560 0.03022 0.0078 0.0160 1.0000
15.000 1.3929 0.03773 0.03242 0.0083 0.0156 1.0000
15.250 1.3916 0.04030 0.03505 0.0087 0.0151 1.0000
15.500 1.3867 0.04334 0.03817 0.0090 0.0147 1.0000
15.750 1.3906 0.04555 0.04046 0.0092 0.0145 1.0000
16.000 1.3908 0.04822 0.04322 0.0092 0.0144 1.0000
16.250 1.3946 0.05057 0.04565 0.0091 0.0140 1.0000
16.500 1.3957 0.05330 0.04846 0.0089 0.0137 1.0000
16.750 1.3955 0.05622 0.05146 0.0085 0.0135 1.0000
17.000 1.3943 0.05933 0.05465 0.0080 0.0133 1.0000
17.250 1.3933 0.06251 0.05791 0.0074 0.0130 1.0000
17.500 1.3895 0.06612 0.06160 0.0066 0.0128 1.0000
17.750 1.3841 0.06998 0.06555 0.0057 0.0126 1.0000
18.000 1.3767 0.07421 0.06985 0.0045 0.0123 1.0000
18.250 1.3701 0.07840 0.07413 0.0033 0.0123 1.0000
18.500 1.3563 0.08365 0.07947 0.0017 0.0121 1.0000
18.750 1.3458 0.08851 0.08443 0.0001 0.0120 1.0000
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