SD7032-099-88 (sd7032-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7032-099-88 (sd7032-il) Reynolds number: 50,000 Max Cl/Cd: 39.85 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7032-il-50000-n5.txt Download as CSV file: xf-sd7032-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD7032-099-88
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3334 0.10082 0.09428 -0.0349 1.0000 0.1094
-8.000 -0.3313 0.09418 0.08761 -0.0366 1.0000 0.0603
-7.750 -0.3385 0.09133 0.08488 -0.0362 1.0000 0.0572
-7.500 -0.3650 0.08812 0.08185 -0.0383 1.0000 0.0519
-7.250 -0.3655 0.08562 0.07943 -0.0364 1.0000 0.0509
-7.000 -0.3704 0.08287 0.07676 -0.0357 1.0000 0.0500
-6.750 -0.3760 0.07990 0.07388 -0.0358 1.0000 0.0491
-6.500 -0.3808 0.07666 0.07070 -0.0364 1.0000 0.0481
-6.250 -0.3841 0.07302 0.06709 -0.0376 1.0000 0.0473
-6.000 -0.3851 0.06906 0.06312 -0.0392 1.0000 0.0465
-5.750 -0.3829 0.06486 0.05885 -0.0411 1.0000 0.0460
-5.500 -0.3772 0.06062 0.05450 -0.0431 1.0000 0.0461
-5.250 -0.3676 0.05637 0.05005 -0.0452 1.0000 0.0465
-5.000 -0.3541 0.05212 0.04550 -0.0474 1.0000 0.0473
-4.750 -0.3224 0.04688 0.03975 -0.0528 0.9953 0.0478
-4.500 -0.2850 0.04192 0.03414 -0.0579 0.9893 0.0480
-4.250 -0.2456 0.03779 0.02931 -0.0621 0.9838 0.0487
-4.000 -0.2074 0.03467 0.02532 -0.0650 0.9773 0.0521
-3.750 -0.1701 0.03238 0.02277 -0.0678 0.9716 0.0562
-3.500 -0.1351 0.03044 0.02042 -0.0694 0.9645 0.0593
-3.250 -0.0964 0.02888 0.01841 -0.0714 0.9584 0.0664
-3.000 -0.0636 0.02763 0.01706 -0.0724 0.9505 0.0730
-2.750 -0.0259 0.02649 0.01573 -0.0741 0.9439 0.0826
-2.500 0.0066 0.02563 0.01475 -0.0750 0.9350 0.0981
-2.250 0.0473 0.02459 0.01374 -0.0775 0.9286 0.1333
-2.000 0.0794 0.02330 0.01313 -0.0791 0.9192 0.2543
-1.750 0.1107 0.02194 0.01312 -0.0798 0.9123 0.5485
-1.500 0.1279 0.02137 0.01316 -0.0759 0.9018 0.7553
-1.250 0.1691 0.02090 0.01266 -0.0771 0.8921 1.0000
-1.000 0.2126 0.02098 0.01228 -0.0802 0.8842 1.0000
-0.750 0.2440 0.02110 0.01207 -0.0810 0.8723 1.0000
-0.500 0.2760 0.02122 0.01189 -0.0819 0.8607 1.0000
-0.250 0.3099 0.02130 0.01170 -0.0829 0.8499 1.0000
0.000 0.3472 0.02130 0.01147 -0.0844 0.8406 1.0000
0.250 0.3767 0.02139 0.01138 -0.0846 0.8279 1.0000
0.500 0.4066 0.02148 0.01129 -0.0848 0.8154 1.0000
0.750 0.4369 0.02154 0.01121 -0.0850 0.8030 1.0000
1.000 0.4678 0.02157 0.01112 -0.0852 0.7908 1.0000
1.250 0.4994 0.02157 0.01100 -0.0855 0.7789 1.0000
1.500 0.5320 0.02151 0.01083 -0.0858 0.7674 1.0000
1.750 0.5607 0.02156 0.01081 -0.0855 0.7537 1.0000
2.000 0.5892 0.02162 0.01080 -0.0852 0.7397 1.0000
2.250 0.6178 0.02167 0.01079 -0.0849 0.7255 1.0000
2.500 0.6462 0.02173 0.01080 -0.0845 0.7111 1.0000
2.750 0.6745 0.02180 0.01082 -0.0841 0.6963 1.0000
3.000 0.7027 0.02188 0.01088 -0.0837 0.6813 1.0000
3.250 0.7307 0.02198 0.01094 -0.0832 0.6660 1.0000
3.500 0.7581 0.02212 0.01104 -0.0827 0.6502 1.0000
3.750 0.7838 0.02235 0.01129 -0.0820 0.6332 1.0000
4.000 0.8097 0.02258 0.01151 -0.0814 0.6162 1.0000
4.250 0.8357 0.02283 0.01175 -0.0807 0.5991 1.0000
4.500 0.8617 0.02309 0.01204 -0.0800 0.5821 1.0000
4.750 0.8876 0.02337 0.01230 -0.0794 0.5650 1.0000
5.000 0.9136 0.02367 0.01258 -0.0787 0.5480 1.0000
5.250 0.9370 0.02410 0.01305 -0.0778 0.5296 1.0000
5.500 0.9607 0.02453 0.01354 -0.0770 0.5115 1.0000
5.750 0.9847 0.02497 0.01400 -0.0761 0.4940 1.0000
6.000 1.0087 0.02542 0.01448 -0.0753 0.4768 1.0000
6.250 1.0325 0.02591 0.01497 -0.0745 0.4600 1.0000
6.500 1.0544 0.02651 0.01569 -0.0736 0.4424 1.0000
6.750 1.0762 0.02712 0.01638 -0.0726 0.4252 1.0000
7.000 1.0978 0.02776 0.01709 -0.0716 0.4083 1.0000
7.250 1.1191 0.02843 0.01783 -0.0706 0.3917 1.0000
7.500 1.1400 0.02913 0.01863 -0.0695 0.3755 1.0000
7.750 1.1604 0.02985 0.01943 -0.0684 0.3593 1.0000
8.000 1.1803 0.03062 0.02026 -0.0673 0.3434 1.0000
8.250 1.1981 0.03148 0.02122 -0.0660 0.3270 1.0000
8.500 1.2150 0.03239 0.02225 -0.0646 0.3108 1.0000
8.750 1.2308 0.03333 0.02336 -0.0631 0.2946 1.0000
9.000 1.2455 0.03433 0.02446 -0.0615 0.2788 1.0000
9.250 1.2590 0.03538 0.02563 -0.0598 0.2634 1.0000
9.500 1.2708 0.03649 0.02685 -0.0579 0.2481 1.0000
9.750 1.2811 0.03769 0.02815 -0.0560 0.2335 1.0000
10.000 1.2890 0.03897 0.02954 -0.0539 0.2194 1.0000
10.250 1.2947 0.04035 0.03106 -0.0516 0.2062 1.0000
10.500 1.2988 0.04188 0.03269 -0.0493 0.1935 1.0000
10.750 1.3020 0.04355 0.03445 -0.0472 0.1815 1.0000
11.000 1.3049 0.04535 0.03629 -0.0453 0.1704 1.0000
11.250 1.3059 0.04737 0.03842 -0.0435 0.1597 1.0000
11.500 1.3058 0.04974 0.04097 -0.0420 0.1495 1.0000
11.750 1.3065 0.05217 0.04351 -0.0407 0.1407 1.0000
12.000 1.3062 0.05463 0.04600 -0.0396 0.1323 1.0000
12.250 1.3025 0.05779 0.04941 -0.0388 0.1244 1.0000
12.500 1.3024 0.06048 0.05209 -0.0382 0.1177 1.0000
12.750 1.2969 0.06426 0.05618 -0.0380 0.1115 1.0000
13.000 1.2975 0.06701 0.05893 -0.0376 0.1056 1.0000
13.250 1.2868 0.07176 0.06402 -0.0383 0.1008 1.0000
13.500 1.2804 0.07585 0.06827 -0.0389 0.0962 1.0000
13.750 1.2788 0.07943 0.07189 -0.0392 0.0919 1.0000
14.000 1.2634 0.08553 0.07834 -0.0412 0.0892 1.0000
14.250 1.2482 0.09178 0.08484 -0.0436 0.0865 1.0000
14.500 1.2387 0.09708 0.09027 -0.0456 0.0834 1.0000
14.750 1.2360 0.10122 0.09443 -0.0469 0.0799 1.0000
15.000 1.2105 0.11042 0.10391 -0.0518 0.0792 1.0000
15.250 1.1798 0.12156 0.11527 -0.0582 0.0792 1.0000
15.500 1.1413 0.13589 0.12967 -0.0668 0.0797 1.0000
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Polar data table (+)
Polar graphs
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