SD7032-099-88 (sd7032-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: SD7032-099-88 (sd7032-il) Reynolds number: 100,000 Max Cl/Cd: 58.02 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7032-il-100000-n5.txt Download as CSV file: xf-sd7032-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3276 0.09961 0.09480 -0.0385 1.0000 0.0516
-8.500 -0.3331 0.09708 0.09237 -0.0394 1.0000 0.0519
-8.250 -0.3364 0.09001 0.08532 -0.0394 1.0000 0.0309
-8.000 -0.3365 0.08776 0.08313 -0.0374 1.0000 0.0299
-7.750 -0.3436 0.08562 0.08107 -0.0358 1.0000 0.0291
-7.500 -0.3568 0.08364 0.07920 -0.0336 1.0000 0.0285
-7.250 -0.3729 0.08194 0.07761 -0.0312 1.0000 0.0279
-6.750 -0.3733 0.06694 0.06260 -0.0478 0.9912 0.0237
-6.500 -0.3500 0.06025 0.05577 -0.0563 0.9843 0.0235
-6.250 -0.3276 0.05212 0.04730 -0.0652 0.9759 0.0237
-6.000 -0.3016 0.04555 0.04034 -0.0722 0.9697 0.0244
-5.750 -0.2767 0.04342 0.03813 -0.0746 0.9628 0.0258
-5.500 -0.2442 0.03729 0.03135 -0.0800 0.9579 0.0257
-5.250 -0.2168 0.03310 0.02655 -0.0822 0.9507 0.0258
-5.000 -0.1829 0.02977 0.02265 -0.0848 0.9458 0.0265
-4.750 -0.1472 0.02714 0.01949 -0.0870 0.9417 0.0279
-4.500 -0.1170 0.02534 0.01716 -0.0876 0.9345 0.0309
-4.250 -0.0814 0.02334 0.01490 -0.0894 0.9304 0.0331
-4.000 -0.0504 0.02203 0.01341 -0.0900 0.9240 0.0354
-3.750 -0.0177 0.02107 0.01223 -0.0908 0.9177 0.0402
-3.500 0.0181 0.01979 0.01092 -0.0923 0.9136 0.0443
-3.250 0.0446 0.01911 0.01017 -0.0920 0.9044 0.0502
-3.000 0.0795 0.01823 0.00922 -0.0932 0.8993 0.0578
-2.750 0.1064 0.01759 0.00853 -0.0929 0.8899 0.0682
-2.500 0.1405 0.01675 0.00783 -0.0940 0.8843 0.1040
-2.250 0.1664 0.01606 0.00743 -0.0937 0.8743 0.1825
-2.000 0.1951 0.01512 0.00720 -0.0942 0.8666 0.3575
-1.750 0.2203 0.01441 0.00713 -0.0934 0.8576 0.5386
-1.500 0.2436 0.01403 0.00705 -0.0917 0.8477 0.6581
-1.250 0.2678 0.01368 0.00687 -0.0898 0.8395 0.7579
-1.000 0.2890 0.01343 0.00670 -0.0873 0.8285 0.8399
-0.750 0.3243 0.01313 0.00638 -0.0879 0.8184 0.9363
-0.500 0.3628 0.01297 0.00602 -0.0897 0.8081 1.0000
-0.250 0.3920 0.01293 0.00579 -0.0898 0.7971 1.0000
0.000 0.4195 0.01294 0.00564 -0.0895 0.7841 1.0000
0.250 0.4472 0.01295 0.00549 -0.0893 0.7710 1.0000
0.500 0.4751 0.01297 0.00537 -0.0890 0.7575 1.0000
0.750 0.5029 0.01301 0.00527 -0.0888 0.7437 1.0000
1.000 0.5306 0.01305 0.00518 -0.0885 0.7293 1.0000
1.250 0.5582 0.01312 0.00512 -0.0882 0.7145 1.0000
1.500 0.5856 0.01320 0.00509 -0.0879 0.6993 1.0000
1.750 0.6129 0.01330 0.00508 -0.0876 0.6837 1.0000
2.000 0.6400 0.01342 0.00509 -0.0872 0.6678 1.0000
2.250 0.6669 0.01357 0.00513 -0.0868 0.6517 1.0000
2.500 0.6935 0.01373 0.00520 -0.0864 0.6351 1.0000
2.750 0.7198 0.01392 0.00532 -0.0860 0.6180 1.0000
3.000 0.7459 0.01412 0.00544 -0.0855 0.6007 1.0000
3.250 0.7719 0.01435 0.00558 -0.0850 0.5834 1.0000
3.500 0.7977 0.01459 0.00576 -0.0846 0.5659 1.0000
3.750 0.8233 0.01485 0.00594 -0.0840 0.5484 1.0000
4.000 0.8485 0.01512 0.00616 -0.0835 0.5303 1.0000
4.250 0.8735 0.01542 0.00640 -0.0830 0.5121 1.0000
4.500 0.8984 0.01573 0.00669 -0.0824 0.4946 1.0000
4.750 0.9230 0.01606 0.00698 -0.0818 0.4773 1.0000
5.000 0.9475 0.01642 0.00728 -0.0812 0.4604 1.0000
5.250 0.9717 0.01679 0.00766 -0.0806 0.4435 1.0000
5.500 0.9957 0.01717 0.00803 -0.0800 0.4266 1.0000
5.750 1.0194 0.01757 0.00843 -0.0793 0.4102 1.0000
6.000 1.0428 0.01800 0.00886 -0.0786 0.3939 1.0000
6.250 1.0660 0.01845 0.00933 -0.0779 0.3780 1.0000
6.500 1.0887 0.01892 0.00981 -0.0771 0.3621 1.0000
6.750 1.1111 0.01941 0.01032 -0.0763 0.3466 1.0000
7.000 1.1330 0.01993 0.01085 -0.0755 0.3309 1.0000
7.250 1.1543 0.02047 0.01144 -0.0746 0.3152 1.0000
7.500 1.1750 0.02105 0.01202 -0.0736 0.2996 1.0000
7.750 1.1955 0.02164 0.01266 -0.0726 0.2838 1.0000
8.000 1.2152 0.02226 0.01333 -0.0715 0.2680 1.0000
8.250 1.2342 0.02292 0.01404 -0.0704 0.2523 1.0000
8.500 1.2525 0.02361 0.01481 -0.0691 0.2368 1.0000
8.750 1.2698 0.02434 0.01559 -0.0678 0.2215 1.0000
9.000 1.2861 0.02512 0.01643 -0.0664 0.2064 1.0000
9.250 1.3013 0.02596 0.01731 -0.0648 0.1917 1.0000
9.500 1.3154 0.02685 0.01826 -0.0632 0.1777 1.0000
9.750 1.3278 0.02779 0.01929 -0.0613 0.1644 1.0000
10.000 1.3380 0.02880 0.02036 -0.0592 0.1521 1.0000
10.250 1.3468 0.02992 0.02154 -0.0570 0.1400 1.0000
10.500 1.3541 0.03117 0.02283 -0.0548 0.1284 1.0000
10.750 1.3596 0.03257 0.02426 -0.0527 0.1181 1.0000
11.000 1.3658 0.03402 0.02583 -0.0507 0.1078 1.0000
11.250 1.3705 0.03564 0.02754 -0.0488 0.0988 1.0000
11.500 1.3723 0.03753 0.02946 -0.0470 0.0915 1.0000
11.750 1.3753 0.03945 0.03155 -0.0454 0.0844 1.0000
12.000 1.3749 0.04172 0.03388 -0.0439 0.0790 1.0000
12.250 1.3764 0.04398 0.03630 -0.0427 0.0733 1.0000
12.500 1.3727 0.04677 0.03912 -0.0417 0.0693 1.0000
12.750 1.3733 0.04939 0.04193 -0.0410 0.0649 1.0000
13.000 1.3711 0.05235 0.04504 -0.0405 0.0610 1.0000
13.250 1.3654 0.05581 0.04855 -0.0404 0.0581 1.0000
13.500 1.3632 0.05911 0.05205 -0.0404 0.0550 1.0000
13.750 1.3595 0.06269 0.05581 -0.0407 0.0519 1.0000
14.000 1.3538 0.06666 0.05991 -0.0414 0.0495 1.0000
14.250 1.3459 0.07099 0.06430 -0.0424 0.0474 1.0000
14.500 1.3407 0.07526 0.06878 -0.0434 0.0452 1.0000
14.750 1.3345 0.07985 0.07358 -0.0448 0.0429 1.0000
15.000 1.3271 0.08474 0.07864 -0.0465 0.0410 1.0000
15.250 1.3185 0.08995 0.08397 -0.0487 0.0393 1.0000
15.500 1.3101 0.09514 0.08921 -0.0508 0.0377 1.0000
15.750 1.3008 0.10091 0.09523 -0.0533 0.0362 1.0000
16.000 1.2903 0.10712 0.10167 -0.0563 0.0347 1.0000
16.250 1.2797 0.11348 0.10823 -0.0595 0.0333 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SD7032-099-88 (sd7032-il)