AH 79-K-132/20 (ah79k132-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AH 79-K-132/20 (ah79k132-il) Reynolds number: 1,000,000 Max Cl/Cd: 130.58 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah79k132-il-1000000.txt Download as CSV file: xf-ah79k132-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-K-132/20
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2261 0.10086 0.09812 -0.0852 0.7716 0.0110
-11.500 -0.2167 0.09894 0.09620 -0.0862 0.7710 0.0115
-11.250 -0.5507 0.03629 0.03333 -0.1107 0.7691 0.0075
-10.750 -0.5764 0.03184 0.02856 -0.1028 0.7670 0.0076
-10.500 -0.5563 0.03195 0.02867 -0.1020 0.7661 0.0079
-10.250 -0.5689 0.02858 0.02497 -0.0980 0.7648 0.0079
-10.000 -0.5540 0.02781 0.02412 -0.0967 0.7642 0.0082
-9.750 -0.5469 0.02592 0.02202 -0.0945 0.7633 0.0085
-9.500 -0.5335 0.02462 0.02056 -0.0929 0.7624 0.0088
-9.250 -0.5177 0.02349 0.01928 -0.0916 0.7613 0.0091
-9.000 -0.4977 0.02283 0.01852 -0.0907 0.7602 0.0096
-8.750 -0.4806 0.02163 0.01714 -0.0894 0.7591 0.0098
-8.500 -0.4587 0.02108 0.01648 -0.0887 0.7580 0.0100
-8.250 -0.4354 0.02072 0.01603 -0.0882 0.7570 0.0102
-8.000 -0.4255 0.01776 0.01263 -0.0859 0.7560 0.0104
-7.750 -0.4082 0.01597 0.01058 -0.0844 0.7550 0.0109
-7.500 -0.3865 0.01501 0.00948 -0.0836 0.7541 0.0113
-7.250 -0.3629 0.01438 0.00877 -0.0831 0.7532 0.0119
-7.000 -0.3382 0.01392 0.00825 -0.0827 0.7523 0.0124
-6.750 -0.3134 0.01357 0.00783 -0.0823 0.7511 0.0131
-6.500 -0.2883 0.01316 0.00737 -0.0820 0.7502 0.0139
-6.250 -0.2634 0.01270 0.00683 -0.0815 0.7492 0.0144
-6.000 -0.2380 0.01233 0.00642 -0.0812 0.7479 0.0148
-5.750 -0.2137 0.01181 0.00582 -0.0807 0.7466 0.0155
-5.500 -0.1895 0.01125 0.00520 -0.0801 0.7453 0.0172
-5.250 -0.1635 0.01095 0.00489 -0.0798 0.7439 0.0190
-5.000 -0.1370 0.01070 0.00462 -0.0797 0.7426 0.0208
-4.750 -0.1110 0.01036 0.00426 -0.0794 0.7414 0.0256
-4.500 -0.0835 0.01023 0.00413 -0.0794 0.7403 0.0302
-4.250 -0.0570 0.00997 0.00388 -0.0793 0.7391 0.0386
-4.000 -0.0293 0.00992 0.00379 -0.0794 0.7378 0.0410
-3.750 -0.0030 0.00971 0.00359 -0.0792 0.7365 0.0470
-3.500 0.0241 0.00957 0.00347 -0.0792 0.7350 0.0515
-3.250 0.0511 0.00940 0.00333 -0.0792 0.7333 0.0577
-3.000 0.0784 0.00926 0.00321 -0.0792 0.7317 0.0646
-2.750 0.1058 0.00910 0.00304 -0.0792 0.7300 0.0720
-2.500 0.1334 0.00895 0.00289 -0.0793 0.7284 0.0799
-2.250 0.1608 0.00876 0.00274 -0.0793 0.7268 0.0927
-2.000 0.1879 0.00855 0.00260 -0.0793 0.7253 0.1177
-1.750 0.2140 0.00829 0.00251 -0.0792 0.7234 0.1770
-1.500 0.2382 0.00784 0.00241 -0.0788 0.7215 0.2805
-1.250 0.2600 0.00717 0.00228 -0.0781 0.7193 0.4505
-1.000 0.2784 0.00634 0.00216 -0.0766 0.7169 0.6722
-0.750 0.3013 0.00601 0.00215 -0.0755 0.7148 0.7763
-0.500 0.3274 0.00597 0.00220 -0.0750 0.7128 0.8215
-0.250 0.3548 0.00602 0.00224 -0.0748 0.7108 0.8458
0.000 0.3820 0.00608 0.00231 -0.0746 0.7084 0.8574
0.250 0.4095 0.00609 0.00234 -0.0745 0.7055 0.8643
0.500 0.4369 0.00613 0.00238 -0.0743 0.7025 0.8722
0.750 0.4632 0.00620 0.00245 -0.0738 0.6998 0.8818
1.000 0.4892 0.00628 0.00253 -0.0732 0.6972 0.8917
1.250 0.5155 0.00632 0.00258 -0.0727 0.6940 0.8965
1.500 0.5430 0.00630 0.00257 -0.0727 0.6900 0.8995
1.750 0.5711 0.00628 0.00254 -0.0729 0.6862 0.9022
2.000 0.5990 0.00625 0.00247 -0.0730 0.6826 0.9045
2.250 0.6259 0.00621 0.00247 -0.0729 0.6774 0.9065
2.500 0.6518 0.00621 0.00247 -0.0724 0.6717 0.9104
2.750 0.6782 0.00623 0.00250 -0.0722 0.6656 0.9144
3.000 0.7056 0.00625 0.00250 -0.0722 0.6583 0.9170
3.250 0.7325 0.00623 0.00248 -0.0722 0.6504 0.9185
3.750 0.7839 0.00627 0.00248 -0.0715 0.6270 0.9220
4.000 0.8090 0.00635 0.00252 -0.0711 0.6130 0.9238
4.250 0.8339 0.00645 0.00258 -0.0707 0.5981 0.9257
4.500 0.8577 0.00660 0.00268 -0.0701 0.5798 0.9281
4.750 0.8815 0.00677 0.00281 -0.0695 0.5625 0.9303
5.000 0.9047 0.00694 0.00292 -0.0687 0.5452 0.9321
5.250 0.9271 0.00710 0.00304 -0.0679 0.5279 0.9341
5.500 0.9493 0.00729 0.00319 -0.0670 0.5095 0.9359
5.750 0.9705 0.00753 0.00338 -0.0659 0.4893 0.9379
6.000 0.9922 0.00775 0.00356 -0.0650 0.4721 0.9398
6.250 1.0136 0.00798 0.00375 -0.0640 0.4535 0.9419
6.500 1.0312 0.00835 0.00401 -0.0624 0.4257 0.9442
6.750 1.0448 0.00880 0.00431 -0.0600 0.3901 0.9469
7.000 1.0516 0.00942 0.00471 -0.0564 0.3424 0.9506
7.250 1.0558 0.01009 0.00516 -0.0524 0.2959 0.9550
7.500 1.0562 0.01069 0.00559 -0.0476 0.2591 0.9606
7.750 1.0598 0.01137 0.00612 -0.0437 0.2234 0.9684
8.000 1.0715 0.01246 0.00698 -0.0424 0.1757 0.9778
8.250 1.0881 0.01410 0.00830 -0.0432 0.1157 1.0000
8.500 1.0947 0.01554 0.00955 -0.0417 0.0798 1.0000
8.750 1.1009 0.01702 0.01083 -0.0401 0.0472 1.0000
9.000 1.1136 0.01805 0.01180 -0.0391 0.0322 1.0000
9.250 1.1167 0.01975 0.01333 -0.0371 0.0087 1.0000
9.500 1.1301 0.02075 0.01437 -0.0361 0.0067 1.0000
9.750 1.1409 0.02195 0.01565 -0.0348 0.0057 1.0000
10.000 1.1562 0.02284 0.01658 -0.0341 0.0054 1.0000
10.250 1.1709 0.02376 0.01755 -0.0333 0.0052 1.0000
10.500 1.1832 0.02487 0.01871 -0.0323 0.0049 1.0000
10.750 1.1948 0.02603 0.01993 -0.0313 0.0047 1.0000
11.000 1.2059 0.02723 0.02117 -0.0303 0.0044 1.0000
11.250 1.2165 0.02848 0.02247 -0.0293 0.0042 1.0000
11.500 1.2246 0.02992 0.02399 -0.0282 0.0040 1.0000
11.750 1.2316 0.03146 0.02561 -0.0269 0.0039 1.0000
12.000 1.2324 0.03353 0.02778 -0.0253 0.0038 1.0000
12.250 1.2366 0.03535 0.02967 -0.0240 0.0037 1.0000
12.500 1.2370 0.03759 0.03201 -0.0226 0.0036 1.0000
12.750 1.2389 0.03978 0.03429 -0.0214 0.0036 1.0000
13.000 1.2390 0.04219 0.03679 -0.0202 0.0036 1.0000
13.250 1.2359 0.04491 0.03961 -0.0188 0.0036 1.0000
13.500 1.2445 0.04665 0.04142 -0.0183 0.0035 1.0000
13.750 1.2394 0.04956 0.04442 -0.0168 0.0035 1.0000
14.000 1.2496 0.05128 0.04622 -0.0167 0.0034 1.0000
14.250 1.2554 0.05339 0.04841 -0.0163 0.0034 1.0000
14.500 1.2559 0.05598 0.05111 -0.0155 0.0034 1.0000
14.750 1.2557 0.05864 0.05387 -0.0147 0.0034 1.0000
15.000 1.2622 0.06089 0.05620 -0.0148 0.0032 1.0000
15.250 1.2590 0.06392 0.05934 -0.0139 0.0033 1.0000
15.500 1.2602 0.06672 0.06225 -0.0137 0.0032 1.0000
15.750 1.2593 0.06970 0.06533 -0.0135 0.0032 1.0000
16.000 1.2585 0.07287 0.06862 -0.0135 0.0031 1.0000
16.250 1.2561 0.07622 0.07208 -0.0135 0.0031 1.0000
16.500 1.2533 0.07977 0.07574 -0.0139 0.0031 1.0000
16.750 1.2487 0.08364 0.07974 -0.0144 0.0029 1.0000
17.000 1.2425 0.08774 0.08397 -0.0149 0.0029 1.0000
17.250 1.2345 0.09220 0.08857 -0.0157 0.0029 1.0000
17.500 1.2259 0.09698 0.09349 -0.0168 0.0029 1.0000
17.750 1.2148 0.10223 0.09888 -0.0183 0.0028 1.0000
18.000 1.2044 0.10758 0.10437 -0.0201 0.0028 1.0000
18.250 1.1914 0.11356 0.11051 -0.0223 0.0028 1.0000
18.500 1.1757 0.12017 0.11729 -0.0249 0.0029 1.0000
18.750 1.1630 0.12657 0.12383 -0.0279 0.0029 1.0000
19.000 1.1479 0.13364 0.13105 -0.0314 0.0029 1.0000
19.250 1.1335 0.14085 0.13840 -0.0353 0.0030 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AH 79-K-132/20 (ah79k132-il)