USA 26 AIRFOIL (usa26-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 26 AIRFOIL (usa26-il) Reynolds number: 200,000 Max Cl/Cd: 69.14 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa26-il-200000-n5.txt Download as CSV file: xf-usa26-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 26 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3545 0.10327 0.09974 -0.0299 1.0000 0.0239
-9.250 -0.3594 0.10004 0.09655 -0.0300 1.0000 0.0241
-9.000 -0.3652 0.09693 0.09348 -0.0299 1.0000 0.0242
-8.500 -0.3703 0.09276 0.08941 -0.0280 1.0000 0.0265
-8.250 -0.3729 0.09109 0.08780 -0.0267 1.0000 0.0276
-8.000 -0.3827 0.08894 0.08570 -0.0254 1.0000 0.0282
-7.750 -0.3756 0.08421 0.08098 -0.0309 0.9954 0.0280
-7.500 -0.3645 0.07902 0.07577 -0.0374 0.9891 0.0281
-7.250 -0.3479 0.07318 0.06988 -0.0448 0.9832 0.0282
-7.000 -0.3309 0.06788 0.06450 -0.0511 0.9767 0.0299
-6.750 -0.3151 0.06155 0.05805 -0.0574 0.9695 0.0308
-6.500 -0.2949 0.05453 0.05084 -0.0635 0.9636 0.0312
-6.000 -0.2614 0.04024 0.03586 -0.0705 0.9500 0.0336
-5.750 -0.2434 0.03767 0.03312 -0.0704 0.9425 0.0342
-5.500 -0.2193 0.03394 0.02904 -0.0716 0.9365 0.0347
-5.250 -0.1973 0.03114 0.02593 -0.0716 0.9285 0.0354
-5.000 -0.1693 0.02899 0.02350 -0.0724 0.9213 0.0369
-4.750 -0.1478 0.02669 0.02083 -0.0715 0.9124 0.0377
-4.500 -0.1211 0.02446 0.01819 -0.0715 0.9059 0.0381
-4.250 -0.0986 0.02283 0.01624 -0.0704 0.8972 0.0386
-4.000 -0.0688 0.02129 0.01438 -0.0708 0.8908 0.0391
-3.750 -0.0434 0.02018 0.01301 -0.0701 0.8814 0.0398
-3.500 -0.0079 0.01920 0.01175 -0.0715 0.8748 0.0411
-3.250 0.0197 0.01830 0.01064 -0.0712 0.8641 0.0416
-3.000 0.0518 0.01738 0.00953 -0.0718 0.8536 0.0418
-2.750 0.0868 0.01655 0.00852 -0.0731 0.8422 0.0422
-2.500 0.1223 0.01555 0.00738 -0.0744 0.8278 0.0429
-2.250 0.1570 0.01468 0.00643 -0.0757 0.8102 0.0439
-2.000 0.1906 0.01409 0.00576 -0.0767 0.7894 0.0448
-1.750 0.2213 0.01365 0.00523 -0.0771 0.7651 0.0459
-1.500 0.2499 0.01338 0.00485 -0.0770 0.7358 0.0480
-1.250 0.2760 0.01320 0.00450 -0.0764 0.6998 0.0501
-1.000 0.2996 0.01309 0.00419 -0.0753 0.6588 0.0516
-0.750 0.3210 0.01307 0.00392 -0.0737 0.6170 0.0529
-0.500 0.3421 0.01310 0.00373 -0.0722 0.5834 0.0543
-0.250 0.3633 0.01305 0.00352 -0.0707 0.5592 0.0569
0.000 0.3854 0.01305 0.00338 -0.0694 0.5405 0.0612
0.250 0.4082 0.01307 0.00326 -0.0683 0.5249 0.0674
0.500 0.4308 0.01298 0.00316 -0.0671 0.5112 0.0830
0.750 0.4503 0.01260 0.00327 -0.0656 0.4992 0.2350
1.000 0.4725 0.01259 0.00335 -0.0645 0.4877 0.2937
1.250 0.4946 0.01260 0.00341 -0.0633 0.4769 0.3401
1.500 0.5157 0.01244 0.00343 -0.0620 0.4662 0.4124
2.000 0.6924 0.01206 0.00410 -0.0881 0.4370 1.0000
2.250 0.7140 0.01223 0.00418 -0.0868 0.4296 1.0000
2.500 0.7359 0.01238 0.00428 -0.0856 0.4221 1.0000
2.750 0.7573 0.01257 0.00439 -0.0843 0.4158 1.0000
3.000 0.7793 0.01272 0.00452 -0.0831 0.4090 1.0000
3.250 0.8005 0.01292 0.00464 -0.0817 0.4024 1.0000
3.500 0.8221 0.01308 0.00479 -0.0805 0.3950 1.0000
3.750 0.8430 0.01328 0.00493 -0.0791 0.3878 1.0000
4.000 0.8644 0.01346 0.00510 -0.0778 0.3808 1.0000
4.250 0.8854 0.01366 0.00528 -0.0765 0.3742 1.0000
4.500 0.9065 0.01387 0.00547 -0.0751 0.3690 1.0000
4.750 0.9283 0.01406 0.00567 -0.0739 0.3637 1.0000
5.000 0.9492 0.01427 0.00589 -0.0726 0.3584 1.0000
5.250 0.9702 0.01450 0.00612 -0.0713 0.3533 1.0000
5.500 0.9917 0.01470 0.00636 -0.0701 0.3481 1.0000
5.750 1.0124 0.01493 0.00660 -0.0687 0.3431 1.0000
6.000 1.0331 0.01516 0.00687 -0.0673 0.3377 1.0000
6.250 1.0533 0.01537 0.00712 -0.0659 0.3305 1.0000
6.500 1.0722 0.01561 0.00737 -0.0642 0.3223 1.0000
6.750 1.0912 0.01583 0.00762 -0.0625 0.3130 1.0000
7.000 1.1099 0.01606 0.00791 -0.0608 0.3034 1.0000
7.250 1.1270 0.01630 0.00816 -0.0588 0.2897 1.0000
7.500 1.1443 0.01656 0.00844 -0.0569 0.2766 1.0000
7.750 1.1613 0.01684 0.00873 -0.0549 0.2596 1.0000
8.000 1.1759 0.01721 0.00904 -0.0526 0.2342 1.0000
8.250 1.1863 0.01781 0.00948 -0.0496 0.1966 1.0000
8.500 1.1930 0.01862 0.01009 -0.0461 0.1682 1.0000
8.750 1.1996 0.01945 0.01080 -0.0426 0.1456 1.0000
9.000 1.2051 0.02037 0.01158 -0.0390 0.1187 1.0000
9.250 1.2073 0.02150 0.01248 -0.0350 0.0761 1.0000
9.500 1.1940 0.02350 0.01408 -0.0291 0.0260 1.0000
9.750 1.1982 0.02460 0.01518 -0.0258 0.0213 1.0000
10.000 1.2062 0.02552 0.01619 -0.0231 0.0196 1.0000
10.250 1.2131 0.02655 0.01736 -0.0204 0.0182 1.0000
10.500 1.2182 0.02772 0.01865 -0.0177 0.0170 1.0000
10.750 1.2220 0.02903 0.02009 -0.0151 0.0161 1.0000
11.000 1.2220 0.03068 0.02189 -0.0123 0.0152 1.0000
11.250 1.2247 0.03221 0.02356 -0.0101 0.0148 1.0000
11.500 1.2272 0.03383 0.02533 -0.0081 0.0146 1.0000
11.750 1.2267 0.03582 0.02747 -0.0063 0.0142 1.0000
12.000 1.2248 0.03806 0.02986 -0.0047 0.0139 1.0000
12.250 1.2218 0.04059 0.03254 -0.0035 0.0137 1.0000
12.500 1.2176 0.04343 0.03555 -0.0028 0.0134 1.0000
12.750 1.2111 0.04674 0.03900 -0.0024 0.0131 1.0000
13.000 1.2059 0.05014 0.04254 -0.0025 0.0129 1.0000
13.250 1.1989 0.05398 0.04650 -0.0030 0.0125 1.0000
13.500 1.1917 0.05800 0.05066 -0.0037 0.0124 1.0000
13.750 1.1844 0.06214 0.05490 -0.0045 0.0121 1.0000
14.000 1.1768 0.06636 0.05922 -0.0054 0.0119 1.0000
14.250 1.1697 0.07051 0.06347 -0.0063 0.0118 1.0000
14.500 1.1616 0.07480 0.06783 -0.0072 0.0115 1.0000
14.750 1.1558 0.07876 0.07185 -0.0080 0.0113 1.0000
15.000 1.1510 0.08250 0.07565 -0.0086 0.0111 1.0000
15.250 1.1483 0.08567 0.07882 -0.0085 0.0108 1.0000
15.500 1.1493 0.08873 0.08197 -0.0090 0.0107 1.0000
15.750 1.1503 0.09186 0.08519 -0.0095 0.0106 1.0000
16.000 1.1526 0.09470 0.08811 -0.0099 0.0105 1.0000
16.250 1.1546 0.09767 0.09120 -0.0103 0.0104 1.0000
16.500 1.1555 0.10095 0.09460 -0.0111 0.0102 1.0000
16.750 1.1575 0.10397 0.09772 -0.0116 0.0101 1.0000
17.000 1.1580 0.10733 0.10120 -0.0125 0.0099 1.0000
17.250 1.1593 0.11056 0.10453 -0.0133 0.0099 1.0000
17.500 1.1569 0.11464 0.10876 -0.0148 0.0095 1.0000
17.750 1.1559 0.11848 0.11273 -0.0162 0.0094 1.0000
18.000 1.1531 0.12275 0.11712 -0.0181 0.0091 1.0000
18.250 1.1508 0.12691 0.12141 -0.0198 0.0090 1.0000
18.500 1.1477 0.13130 0.12593 -0.0219 0.0089 1.0000
18.750 1.1436 0.13600 0.13077 -0.0242 0.0088 1.0000
19.000 1.1412 0.14034 0.13518 -0.0265 0.0085 1.0000
19.250 1.1366 0.14530 0.14029 -0.0292 0.0085 1.0000
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