RAF 31 AIRFOIL (raf31-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 31 AIRFOIL (raf31-il) Reynolds number: 200,000 Max Cl/Cd: 72.09 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf31-il-200000.txt Download as CSV file: xf-raf31-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 31 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4648 0.09905 0.09524 -0.0421 1.0000 0.0859
-10.500 -0.6335 0.06211 0.05817 -0.0693 1.0000 0.0580
-10.250 -0.6549 0.05858 0.05461 -0.0681 1.0000 0.0572
-10.000 -0.6834 0.05556 0.05153 -0.0643 1.0000 0.0563
-9.750 -0.7847 0.04715 0.04222 -0.0540 1.0000 0.0504
-9.500 -0.7923 0.04573 0.04059 -0.0496 1.0000 0.0501
-9.250 -0.7981 0.04285 0.03752 -0.0460 1.0000 0.0498
-9.000 -0.8026 0.04007 0.03450 -0.0425 1.0000 0.0497
-8.750 -0.8034 0.03770 0.03185 -0.0392 1.0000 0.0497
-8.500 -0.8000 0.03539 0.02920 -0.0366 0.9996 0.0502
-8.250 -0.7740 0.03173 0.02522 -0.0383 0.9956 0.0510
-8.000 -0.7440 0.02943 0.02266 -0.0400 0.9916 0.0516
-7.750 -0.7127 0.02758 0.02061 -0.0415 0.9872 0.0523
-7.500 -0.6779 0.02624 0.01909 -0.0436 0.9838 0.0537
-7.250 -0.6480 0.02507 0.01777 -0.0445 0.9785 0.0553
-7.000 -0.6143 0.02374 0.01625 -0.0461 0.9743 0.0565
-6.750 -0.5771 0.02253 0.01487 -0.0482 0.9715 0.0577
-6.500 -0.5486 0.02159 0.01380 -0.0485 0.9650 0.0588
-6.250 -0.5147 0.02037 0.01256 -0.0501 0.9611 0.0610
-6.000 -0.4774 0.01957 0.01178 -0.0524 0.9583 0.0638
-5.750 -0.4512 0.01892 0.01111 -0.0523 0.9511 0.0663
-5.500 -0.4147 0.01823 0.01034 -0.0541 0.9471 0.0697
-5.250 -0.3764 0.01724 0.00941 -0.0566 0.9443 0.0752
-5.000 -0.3499 0.01671 0.00885 -0.0564 0.9362 0.0834
-4.750 -0.3150 0.01557 0.00787 -0.0582 0.9324 0.1119
-4.500 -0.2768 0.01454 0.00718 -0.0608 0.9300 0.1704
-4.250 -0.2526 0.01398 0.00688 -0.0604 0.9221 0.2323
-4.000 -0.2173 0.01338 0.00658 -0.0621 0.9181 0.3075
-3.750 -0.1789 0.01296 0.00633 -0.0643 0.9152 0.3706
-3.500 -0.1541 0.01279 0.00625 -0.0637 0.9075 0.4092
-3.250 -0.1207 0.01251 0.00607 -0.0648 0.9027 0.4472
-3.000 -0.0837 0.01223 0.00586 -0.0664 0.8991 0.4843
-2.750 -0.0620 0.01215 0.00587 -0.0650 0.8900 0.5148
-2.500 -0.0295 0.01197 0.00575 -0.0657 0.8851 0.5523
-2.250 -0.0062 0.01191 0.00579 -0.0645 0.8771 0.5871
-2.000 0.0228 0.01176 0.00571 -0.0644 0.8706 0.6191
-1.750 0.0489 0.01168 0.00568 -0.0637 0.8635 0.6472
-1.500 0.0744 0.01159 0.00567 -0.0628 0.8563 0.6751
-1.250 0.1036 0.01148 0.00561 -0.0626 0.8508 0.7048
-1.000 0.1247 0.01146 0.00566 -0.0609 0.8421 0.7327
-0.750 0.1539 0.01135 0.00558 -0.0606 0.8368 0.7611
-0.500 0.1755 0.01131 0.00564 -0.0589 0.8282 0.7874
-0.250 0.2039 0.01117 0.00553 -0.0584 0.8217 0.8152
0.000 0.2277 0.01110 0.00553 -0.0571 0.8133 0.8439
0.250 0.2598 0.01097 0.00545 -0.0573 0.8066 0.8716
0.500 0.2951 0.01094 0.00546 -0.0584 0.7996 0.8965
0.750 0.3382 0.01093 0.00545 -0.0612 0.7927 0.9165
1.000 0.3849 0.01093 0.00543 -0.0647 0.7863 0.9327
1.250 0.4300 0.01096 0.00546 -0.0681 0.7780 0.9472
1.500 0.4760 0.01097 0.00543 -0.0716 0.7700 0.9593
1.750 0.5202 0.01096 0.00539 -0.0748 0.7600 0.9716
2.000 0.5649 0.01096 0.00538 -0.0783 0.7492 0.9834
2.250 0.6125 0.01092 0.00530 -0.0823 0.7390 0.9932
2.500 0.6521 0.01086 0.00522 -0.0850 0.7274 1.0000
2.750 0.6664 0.01083 0.00518 -0.0825 0.7139 1.0000
3.000 0.6827 0.01082 0.00511 -0.0802 0.6983 1.0000
3.250 0.7004 0.01083 0.00505 -0.0780 0.6813 1.0000
3.500 0.7192 0.01087 0.00502 -0.0760 0.6642 1.0000
3.750 0.7388 0.01093 0.00503 -0.0742 0.6466 1.0000
4.000 0.7574 0.01102 0.00509 -0.0722 0.6273 1.0000
4.250 0.7764 0.01112 0.00515 -0.0702 0.6066 1.0000
4.500 0.7958 0.01124 0.00522 -0.0683 0.5858 1.0000
4.750 0.8149 0.01140 0.00533 -0.0664 0.5639 1.0000
5.000 0.8337 0.01159 0.00545 -0.0645 0.5405 1.0000
5.250 0.8521 0.01182 0.00560 -0.0624 0.5166 1.0000
5.500 0.8697 0.01211 0.00580 -0.0603 0.4921 1.0000
5.750 0.8872 0.01244 0.00604 -0.0582 0.4679 1.0000
6.000 0.9041 0.01284 0.00632 -0.0560 0.4445 1.0000
6.250 0.9207 0.01322 0.00665 -0.0538 0.4190 1.0000
6.500 0.9359 0.01364 0.00701 -0.0513 0.3882 1.0000
6.750 0.9479 0.01410 0.00733 -0.0483 0.3359 1.0000
7.000 0.9494 0.01506 0.00783 -0.0437 0.2689 1.0000
7.250 0.9532 0.01611 0.00858 -0.0396 0.2121 1.0000
7.500 0.9581 0.01713 0.00926 -0.0358 0.1697 1.0000
7.750 0.9643 0.01806 0.01003 -0.0322 0.1528 1.0000
8.000 0.9725 0.01888 0.01079 -0.0289 0.1417 1.0000
8.250 0.9835 0.01962 0.01152 -0.0262 0.1324 1.0000
8.500 0.9922 0.02055 0.01236 -0.0233 0.1243 1.0000
8.750 1.0066 0.02117 0.01304 -0.0213 0.1170 1.0000
9.000 1.0168 0.02217 0.01396 -0.0189 0.1105 1.0000
9.250 1.0321 0.02274 0.01464 -0.0172 0.1047 1.0000
9.500 1.0443 0.02360 0.01548 -0.0152 0.0993 1.0000
9.750 1.0579 0.02445 0.01640 -0.0134 0.0943 1.0000
10.000 1.0712 0.02515 0.01718 -0.0116 0.0887 1.0000
10.250 1.0819 0.02621 0.01822 -0.0098 0.0828 1.0000
10.500 1.0938 0.02690 0.01904 -0.0080 0.0762 1.0000
10.750 1.1026 0.02804 0.02020 -0.0061 0.0694 1.0000
11.000 1.1092 0.02925 0.02139 -0.0042 0.0616 1.0000
11.250 1.1175 0.03048 0.02271 -0.0024 0.0541 1.0000
11.500 1.1237 0.03206 0.02428 -0.0005 0.0496 1.0000
11.750 1.1324 0.03335 0.02566 0.0010 0.0454 1.0000
12.000 1.1380 0.03505 0.02732 0.0026 0.0422 1.0000
12.250 1.1475 0.03652 0.02895 0.0040 0.0399 1.0000
12.500 1.1561 0.03807 0.03057 0.0053 0.0380 1.0000
12.750 1.1637 0.03970 0.03220 0.0065 0.0365 1.0000
13.000 1.1721 0.04159 0.03413 0.0077 0.0350 1.0000
13.250 1.1797 0.04343 0.03617 0.0089 0.0337 1.0000
13.500 1.1867 0.04531 0.03819 0.0099 0.0326 1.0000
13.750 1.1914 0.04717 0.04013 0.0107 0.0313 1.0000
14.000 1.1977 0.04915 0.04216 0.0115 0.0305 1.0000
14.250 1.2063 0.05143 0.04445 0.0124 0.0296 1.0000
14.500 1.2084 0.05419 0.04742 0.0133 0.0291 1.0000
14.750 1.2082 0.05704 0.05049 0.0139 0.0289 1.0000
15.000 1.2021 0.06049 0.05421 0.0143 0.0284 1.0000
15.250 1.1958 0.06416 0.05811 0.0144 0.0282 1.0000
15.500 1.1863 0.06824 0.06244 0.0141 0.0280 1.0000
15.750 1.1729 0.07293 0.06737 0.0133 0.0278 1.0000
16.000 1.1574 0.07815 0.07283 0.0119 0.0278 1.0000
16.250 1.1383 0.08413 0.07906 0.0097 0.0276 1.0000
16.500 1.1169 0.09090 0.08607 0.0068 0.0278 1.0000
16.750 1.0910 0.09891 0.09431 0.0026 0.0277 1.0000
17.000 1.0630 0.10791 0.10353 -0.0024 0.0281 1.0000
17.250 1.0326 0.11805 0.11388 -0.0085 0.0285 1.0000
17.500 0.9973 0.13021 0.12622 -0.0161 0.0289 1.0000
17.750 0.9611 0.14371 0.13985 -0.0244 0.0295 1.0000
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