RAF 26 AIRFOIL (raf26-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 26 AIRFOIL (raf26-il) Reynolds number: 1,000,000 Max Cl/Cd: 94.08 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf26-il-1000000.txt Download as CSV file: xf-raf26-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 26 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4219 0.09515 0.09358 -0.0190 1.0000 0.0079
-9.750 -0.4253 0.09045 0.08890 -0.0199 1.0000 0.0080
-9.500 -0.4283 0.08600 0.08446 -0.0208 1.0000 0.0082
-9.250 -0.4303 0.08191 0.08037 -0.0215 1.0000 0.0083
-9.000 -0.4315 0.07818 0.07665 -0.0221 1.0000 0.0084
-8.750 -0.4311 0.07507 0.07355 -0.0225 1.0000 0.0088
-8.500 -0.4361 0.07058 0.06909 -0.0235 1.0000 0.0087
-8.250 -0.4401 0.06678 0.06530 -0.0241 1.0000 0.0090
-8.000 -0.4494 0.06222 0.06076 -0.0251 1.0000 0.0089
-7.750 -0.4620 0.05833 0.05690 -0.0254 1.0000 0.0090
-5.500 -0.4269 0.01503 0.01067 -0.0459 0.9923 0.0081
-5.250 -0.3992 0.01269 0.00800 -0.0461 0.9900 0.0084
-5.000 -0.3683 0.01142 0.00657 -0.0470 0.9878 0.0090
-4.750 -0.3348 0.01075 0.00582 -0.0483 0.9859 0.0099
-4.500 -0.3004 0.01020 0.00520 -0.0498 0.9844 0.0110
-4.250 -0.2695 0.00966 0.00458 -0.0505 0.9815 0.0118
-4.000 -0.2401 0.00919 0.00404 -0.0508 0.9771 0.0123
-3.750 -0.2091 0.00829 0.00302 -0.0515 0.9738 0.0153
-3.500 -0.1753 0.00798 0.00268 -0.0528 0.9716 0.0179
-3.250 -0.1493 0.00772 0.00239 -0.0523 0.9639 0.0195
-3.000 -0.1181 0.00726 0.00189 -0.0529 0.9591 0.0289
-2.750 -0.0910 0.00694 0.00160 -0.0527 0.9497 0.0430
-2.500 -0.0571 0.00656 0.00136 -0.0541 0.9430 0.0815
-2.250 -0.0153 0.00615 0.00113 -0.0573 0.9341 0.1351
-2.000 0.0277 0.00562 0.00096 -0.0611 0.9271 0.2509
-1.750 0.0702 0.00519 0.00085 -0.0648 0.9169 0.3671
-1.500 0.1069 0.00500 0.00077 -0.0669 0.9012 0.4320
-1.250 0.1360 0.00487 0.00073 -0.0672 0.8844 0.4895
-1.000 0.1616 0.00472 0.00072 -0.0667 0.8694 0.5585
-0.750 0.1847 0.00447 0.00073 -0.0656 0.8556 0.6570
-0.500 0.2065 0.00429 0.00073 -0.0641 0.8374 0.7399
-0.250 0.2270 0.00408 0.00074 -0.0623 0.8183 0.8318
0.000 0.3133 0.00395 0.00082 -0.0755 0.7875 0.9807
0.250 0.3545 0.00414 0.00085 -0.0785 0.7541 0.9977
0.500 0.3855 0.00429 0.00085 -0.0792 0.7185 1.0000
0.750 0.4073 0.00444 0.00086 -0.0778 0.6844 1.0000
1.000 0.4295 0.00461 0.00088 -0.0765 0.6497 1.0000
1.250 0.4516 0.00480 0.00093 -0.0752 0.6132 1.0000
1.500 0.4729 0.00505 0.00098 -0.0738 0.5578 1.0000
1.750 0.4889 0.00572 0.00112 -0.0714 0.4278 1.0000
2.000 0.5105 0.00606 0.00126 -0.0701 0.3769 1.0000
2.250 0.5271 0.00682 0.00147 -0.0680 0.2343 1.0000
2.500 0.5461 0.00743 0.00171 -0.0663 0.1448 1.0000
2.750 0.5673 0.00788 0.00191 -0.0650 0.0887 1.0000
3.000 0.5911 0.00810 0.00210 -0.0641 0.0799 1.0000
3.250 0.6156 0.00826 0.00229 -0.0634 0.0757 1.0000
3.500 0.6393 0.00850 0.00251 -0.0625 0.0685 1.0000
3.750 0.6643 0.00862 0.00265 -0.0619 0.0650 1.0000
4.000 0.6888 0.00879 0.00279 -0.0612 0.0559 1.0000
4.250 0.7108 0.00920 0.00302 -0.0600 0.0230 1.0000
4.500 0.7334 0.00959 0.00339 -0.0589 0.0160 1.0000
4.750 0.7554 0.01006 0.00394 -0.0575 0.0133 1.0000
5.000 0.7784 0.01041 0.00434 -0.0565 0.0123 1.0000
5.250 0.8007 0.01084 0.00483 -0.0553 0.0113 1.0000
5.500 0.8226 0.01131 0.00534 -0.0540 0.0100 1.0000
5.750 0.8402 0.01229 0.00645 -0.0519 0.0087 1.0000
6.000 0.8580 0.01335 0.00764 -0.0498 0.0082 1.0000
6.250 0.8791 0.01404 0.00840 -0.0485 0.0080 1.0000
6.500 0.9008 0.01467 0.00912 -0.0472 0.0076 1.0000
6.750 0.9219 0.01546 0.01000 -0.0459 0.0072 1.0000
7.000 0.9432 0.01623 0.01085 -0.0447 0.0066 1.0000
7.250 0.9637 0.01721 0.01194 -0.0433 0.0063 1.0000
7.500 0.9841 0.01817 0.01303 -0.0420 0.0059 1.0000
7.750 1.0030 0.01946 0.01446 -0.0404 0.0056 1.0000
8.000 1.0194 0.02146 0.01670 -0.0384 0.0055 1.0000
8.250 1.0040 0.03203 0.02848 -0.0303 0.0069 1.0000
8.500 1.0479 0.02572 0.02146 -0.0340 0.0054 1.0000
8.750 1.0566 0.02857 0.02464 -0.0312 0.0053 1.0000
14.750 0.6848 0.16904 0.16761 -0.0623 0.0079 1.0000
15.000 0.6874 0.17319 0.17176 -0.0647 0.0070 1.0000
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Polar data table (+)
Polar graphs
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