SA7035 (sa7035-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7035 (sa7035-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.4 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7035-il-1000000.txt Download as CSV file: xf-sa7035-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: SA7035
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3394 0.08673 0.08522 -0.0282 1.0000 0.0084
-9.500 -0.3390 0.08265 0.08115 -0.0294 1.0000 0.0085
-9.250 -0.3392 0.07830 0.07681 -0.0308 1.0000 0.0085
-9.000 -0.3397 0.07429 0.07281 -0.0320 1.0000 0.0086
-8.750 -0.3409 0.07011 0.06865 -0.0333 1.0000 0.0087
-8.500 -0.3425 0.06616 0.06472 -0.0345 1.0000 0.0089
-8.250 -0.3486 0.06131 0.05990 -0.0362 1.0000 0.0088
-8.000 -0.3578 0.05693 0.05554 -0.0372 1.0000 0.0089
-7.500 -0.4325 0.05073 0.04916 -0.0572 0.9935 0.0084
-7.250 -0.4161 0.04183 0.03999 -0.0656 0.9878 0.0085
-7.000 -0.3916 0.03771 0.03568 -0.0704 0.9849 0.0088
-6.750 -0.3689 0.03340 0.03111 -0.0734 0.9797 0.0090
-6.500 -0.3471 0.03000 0.02747 -0.0750 0.9735 0.0094
-6.250 -0.3271 0.02678 0.02397 -0.0753 0.9663 0.0098
-6.000 -0.3084 0.02399 0.02088 -0.0745 0.9584 0.0105
-5.750 -0.2955 0.01716 0.01318 -0.0717 0.9485 0.0074
-5.500 -0.2759 0.01385 0.00937 -0.0700 0.9418 0.0066
-5.250 -0.2523 0.01250 0.00781 -0.0690 0.9345 0.0067
-5.000 -0.2279 0.01171 0.00687 -0.0682 0.9282 0.0073
-4.750 -0.2023 0.01110 0.00616 -0.0676 0.9206 0.0077
-4.500 -0.1766 0.01067 0.00562 -0.0670 0.9140 0.0080
-4.250 -0.1511 0.00991 0.00477 -0.0664 0.9061 0.0082
-4.000 -0.1260 0.00907 0.00381 -0.0658 0.8989 0.0086
-3.750 -0.0996 0.00859 0.00328 -0.0655 0.8906 0.0093
-3.500 -0.0728 0.00829 0.00292 -0.0652 0.8826 0.0101
-3.250 -0.0458 0.00795 0.00249 -0.0648 0.8736 0.0107
-3.000 -0.0184 0.00769 0.00215 -0.0645 0.8636 0.0116
-2.750 0.0088 0.00729 0.00172 -0.0642 0.8534 0.0224
-2.500 0.0353 0.00685 0.00148 -0.0640 0.8421 0.0840
-2.250 0.0622 0.00655 0.00133 -0.0638 0.8298 0.1417
-2.000 0.0889 0.00619 0.00120 -0.0638 0.8167 0.2256
-1.750 0.1152 0.00572 0.00110 -0.0637 0.8027 0.3526
-1.500 0.1419 0.00544 0.00103 -0.0635 0.7879 0.4417
-1.250 0.1689 0.00526 0.00098 -0.0634 0.7718 0.5084
-1.000 0.1958 0.00510 0.00095 -0.0632 0.7544 0.5817
-0.750 0.2227 0.00500 0.00093 -0.0629 0.7361 0.6382
-0.500 0.2492 0.00490 0.00092 -0.0626 0.7181 0.6984
-0.250 0.2757 0.00482 0.00093 -0.0622 0.7005 0.7539
0.000 0.3018 0.00476 0.00095 -0.0617 0.6827 0.8022
0.250 0.3271 0.00471 0.00098 -0.0609 0.6648 0.8512
0.500 0.3508 0.00470 0.00101 -0.0598 0.6467 0.9006
0.750 0.3746 0.00471 0.00104 -0.0586 0.6285 0.9466
1.000 0.4074 0.00479 0.00105 -0.0595 0.6079 0.9772
1.250 0.4454 0.00490 0.00105 -0.0618 0.5855 0.9947
1.500 0.4772 0.00503 0.00107 -0.0627 0.5633 1.0000
1.750 0.5031 0.00516 0.00112 -0.0623 0.5437 1.0000
2.000 0.5293 0.00530 0.00117 -0.0620 0.5246 1.0000
2.500 0.5821 0.00560 0.00130 -0.0615 0.4856 1.0000
2.750 0.6087 0.00576 0.00138 -0.0612 0.4656 1.0000
3.000 0.6352 0.00594 0.00147 -0.0610 0.4453 1.0000
3.250 0.6617 0.00612 0.00158 -0.0608 0.4231 1.0000
3.500 0.6883 0.00632 0.00169 -0.0606 0.4027 1.0000
3.750 0.7149 0.00650 0.00180 -0.0604 0.3831 1.0000
4.000 0.7413 0.00672 0.00193 -0.0602 0.3627 1.0000
4.250 0.7679 0.00691 0.00207 -0.0601 0.3444 1.0000
4.500 0.7943 0.00713 0.00222 -0.0599 0.3252 1.0000
4.750 0.8205 0.00737 0.00238 -0.0597 0.3047 1.0000
5.000 0.8466 0.00763 0.00256 -0.0594 0.2833 1.0000
5.250 0.8724 0.00791 0.00276 -0.0592 0.2602 1.0000
5.750 0.9238 0.00849 0.00319 -0.0587 0.2198 1.0000
6.000 0.9494 0.00879 0.00342 -0.0584 0.2006 1.0000
6.250 0.9746 0.00914 0.00369 -0.0581 0.1806 1.0000
6.500 0.9999 0.00945 0.00395 -0.0578 0.1634 1.0000
6.750 1.0243 0.00987 0.00427 -0.0574 0.1420 1.0000
7.000 1.0488 0.01027 0.00458 -0.0570 0.1219 1.0000
7.250 1.0730 0.01071 0.00494 -0.0565 0.1040 1.0000
7.500 1.0969 0.01115 0.00531 -0.0560 0.0869 1.0000
7.750 1.1206 0.01161 0.00571 -0.0555 0.0718 1.0000
8.000 1.1436 0.01213 0.00615 -0.0549 0.0565 1.0000
8.250 1.1662 0.01269 0.00663 -0.0543 0.0432 1.0000
8.500 1.1890 0.01321 0.00711 -0.0537 0.0343 1.0000
8.750 1.2119 0.01369 0.00760 -0.0530 0.0275 1.0000
9.000 1.2340 0.01424 0.00814 -0.0523 0.0210 1.0000
9.250 1.2551 0.01488 0.00876 -0.0514 0.0154 1.0000
9.500 1.2756 0.01556 0.00944 -0.0505 0.0116 1.0000
9.750 1.2966 0.01615 0.01009 -0.0496 0.0098 1.0000
10.000 1.3165 0.01682 0.01078 -0.0485 0.0082 1.0000
10.250 1.3345 0.01764 0.01168 -0.0472 0.0068 1.0000
10.500 1.3544 0.01822 0.01233 -0.0462 0.0061 1.0000
10.750 1.3721 0.01895 0.01311 -0.0450 0.0054 1.0000
11.000 1.3815 0.02034 0.01465 -0.0425 0.0045 1.0000
11.250 1.3982 0.02101 0.01538 -0.0410 0.0043 1.0000
11.500 1.4104 0.02180 0.01627 -0.0389 0.0040 1.0000
11.750 1.4204 0.02261 0.01716 -0.0365 0.0038 1.0000
12.000 1.4297 0.02347 0.01809 -0.0341 0.0035 1.0000
12.250 1.4365 0.02452 0.01923 -0.0316 0.0033 1.0000
12.500 1.4418 0.02572 0.02052 -0.0292 0.0032 1.0000
12.750 1.4406 0.02745 0.02236 -0.0264 0.0029 1.0000
13.000 1.4370 0.02948 0.02454 -0.0238 0.0029 1.0000
13.250 1.4277 0.03216 0.02741 -0.0213 0.0028 1.0000
13.500 1.4178 0.03518 0.03059 -0.0196 0.0027 1.0000
13.750 1.4151 0.03780 0.03334 -0.0187 0.0027 1.0000
14.000 1.4237 0.03941 0.03504 -0.0184 0.0026 1.0000
14.250 1.4206 0.04243 0.03818 -0.0182 0.0025 1.0000
14.500 1.4156 0.04587 0.04176 -0.0185 0.0025 1.0000
14.750 1.4078 0.04995 0.04598 -0.0194 0.0025 1.0000
15.000 1.3976 0.05463 0.05081 -0.0208 0.0024 1.0000
15.250 1.3945 0.05857 0.05485 -0.0222 0.0023 1.0000
15.500 1.3816 0.06426 0.06070 -0.0246 0.0023 1.0000
15.750 1.3680 0.07034 0.06692 -0.0275 0.0022 1.0000
16.000 1.3509 0.07733 0.07406 -0.0309 0.0023 1.0000
16.250 1.3360 0.08423 0.08110 -0.0344 0.0023 1.0000
16.500 1.3244 0.09081 0.08780 -0.0379 0.0022 1.0000
16.750 1.2984 0.10028 0.09744 -0.0430 0.0023 1.0000
17.000 1.2845 0.10776 0.10504 -0.0471 0.0022 1.0000
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