GOE 652 AIRFOIL (goe652-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 652 AIRFOIL (goe652-il) Reynolds number: 500,000 Max Cl/Cd: 112.71 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe652-il-500000.txt Download as CSV file: xf-goe652-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 652 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.3256 0.09228 0.08877 -0.1590 0.8604 0.0669
-9.750 -0.0193 0.04175 0.03753 -0.1864 0.8335 0.0654
-9.500 -0.0241 0.03957 0.03527 -0.1869 0.8259 0.0658
-9.250 -0.0208 0.03759 0.03326 -0.1881 0.8196 0.0663
-9.000 -0.0142 0.03563 0.03128 -0.1898 0.8132 0.0669
-8.750 -0.0039 0.03327 0.02883 -0.1931 0.8070 0.0675
-8.500 0.0138 0.03088 0.02631 -0.1980 0.8009 0.0682
-8.250 0.0339 0.02844 0.02381 -0.2031 0.7956 0.0690
-8.000 0.0633 0.02586 0.02110 -0.2101 0.7903 0.0700
-7.750 0.1013 0.02336 0.01841 -0.2183 0.7856 0.0709
-7.500 0.1331 0.02273 0.01778 -0.2203 0.7811 0.0722
-7.250 0.1694 0.02154 0.01657 -0.2247 0.7769 0.0736
-7.000 0.2089 0.02008 0.01505 -0.2301 0.7726 0.0752
-6.750 0.2525 0.01845 0.01329 -0.2365 0.7679 0.0768
-6.500 0.2919 0.01742 0.01220 -0.2406 0.7629 0.0786
-6.250 0.3334 0.01639 0.01108 -0.2452 0.7574 0.0806
-6.000 0.3743 0.01524 0.00985 -0.2496 0.7524 0.0830
-5.750 0.4137 0.01430 0.00885 -0.2533 0.7469 0.0856
-5.500 0.4500 0.01370 0.00818 -0.2557 0.7414 0.0885
-5.250 0.4857 0.01327 0.00761 -0.2576 0.7361 0.0919
-5.000 0.5200 0.01285 0.00720 -0.2593 0.7315 0.0958
-4.750 0.5532 0.01251 0.00680 -0.2605 0.7265 0.1000
-4.500 0.5862 0.01220 0.00649 -0.2617 0.7212 0.1044
-4.250 0.6188 0.01198 0.00616 -0.2626 0.7155 0.1092
-4.000 0.6503 0.01179 0.00596 -0.2632 0.7096 0.1141
-3.750 0.6816 0.01159 0.00575 -0.2638 0.7035 0.1191
-3.500 0.7123 0.01148 0.00559 -0.2641 0.6976 0.1243
-3.250 0.7434 0.01141 0.00544 -0.2646 0.6919 0.1294
-3.000 0.7734 0.01132 0.00537 -0.2648 0.6864 0.1344
-2.750 0.8037 0.01122 0.00524 -0.2650 0.6800 0.1393
-2.500 0.8334 0.01121 0.00518 -0.2650 0.6738 0.1442
-2.250 0.8632 0.01120 0.00511 -0.2651 0.6678 0.1491
-2.000 0.8926 0.01115 0.00511 -0.2651 0.6612 0.1541
-1.750 0.9217 0.01119 0.00507 -0.2650 0.6544 0.1591
-1.500 0.9510 0.01120 0.00504 -0.2650 0.6480 0.1640
-1.250 0.9798 0.01122 0.00509 -0.2649 0.6417 0.1690
-1.000 1.0084 0.01130 0.00509 -0.2646 0.6349 0.1736
-0.500 1.0654 0.01140 0.00520 -0.2642 0.6219 0.1842
-0.250 1.0936 0.01150 0.00522 -0.2639 0.6150 0.1882
0.000 1.1220 0.01152 0.00523 -0.2638 0.6085 0.1934
0.250 1.1502 0.01159 0.00532 -0.2635 0.6024 0.1979
0.500 1.1781 0.01168 0.00537 -0.2632 0.5956 0.2023
0.750 1.2060 0.01174 0.00537 -0.2629 0.5888 0.2067
1.000 1.2338 0.01181 0.00547 -0.2626 0.5825 0.2112
1.250 1.2612 0.01191 0.00557 -0.2622 0.5755 0.2155
1.500 1.2877 0.01207 0.00565 -0.2616 0.5681 0.2195
1.750 1.3152 0.01212 0.00569 -0.2612 0.5604 0.2240
2.000 1.3415 0.01222 0.00580 -0.2607 0.5516 0.2284
2.250 1.3670 0.01241 0.00594 -0.2599 0.5431 0.2327
2.500 1.3933 0.01253 0.00606 -0.2593 0.5347 0.2370
2.750 1.4181 0.01274 0.00618 -0.2585 0.5260 0.2405
3.000 1.4444 0.01282 0.00630 -0.2579 0.5174 0.2460
3.250 1.4682 0.01304 0.00649 -0.2569 0.5069 0.2503
3.500 1.4923 0.01324 0.00667 -0.2559 0.4959 0.2550
3.750 1.5137 0.01356 0.00688 -0.2545 0.4829 0.2586
4.000 1.5366 0.01375 0.00706 -0.2534 0.4681 0.2638
4.250 1.5569 0.01407 0.00734 -0.2518 0.4521 0.2686
4.500 1.5752 0.01447 0.00766 -0.2498 0.4350 0.2731
4.750 1.5903 0.01491 0.00801 -0.2473 0.4182 0.2773
5.000 1.6026 0.01543 0.00841 -0.2443 0.4029 0.2808
5.250 1.6184 0.01585 0.00882 -0.2421 0.3905 0.2868
5.500 1.6329 0.01638 0.00930 -0.2396 0.3808 0.2917
5.750 1.6490 0.01687 0.00976 -0.2375 0.3730 0.2968
6.000 1.6628 0.01748 0.01031 -0.2350 0.3661 0.3013
6.250 1.6809 0.01791 0.01079 -0.2333 0.3609 0.3079
6.500 1.6978 0.01843 0.01131 -0.2314 0.3555 0.3139
6.750 1.7121 0.01908 0.01194 -0.2291 0.3501 0.3197
7.000 1.7256 0.01982 0.01263 -0.2268 0.3450 0.3245
7.250 1.7450 0.02024 0.01314 -0.2255 0.3420 0.3317
7.500 1.7624 0.02079 0.01373 -0.2238 0.3385 0.3385
7.750 1.7785 0.02144 0.01439 -0.2220 0.3349 0.3447
8.000 1.7937 0.02215 0.01512 -0.2202 0.3315 0.3513
8.250 1.8077 0.02298 0.01595 -0.2182 0.3279 0.3575
8.500 1.8237 0.02372 0.01671 -0.2165 0.3249 0.3641
8.750 1.8416 0.02431 0.01737 -0.2151 0.3223 0.3709
9.000 1.8583 0.02497 0.01811 -0.2136 0.3192 0.3781
9.250 1.8731 0.02579 0.01895 -0.2119 0.3156 0.3851
9.500 1.8868 0.02671 0.01987 -0.2102 0.3120 0.3914
9.750 1.8990 0.02778 0.02096 -0.2083 0.3079 0.3979
10.000 1.9145 0.02861 0.02185 -0.2069 0.3049 0.4052
10.250 1.9304 0.02940 0.02272 -0.2055 0.3018 0.4127
10.500 1.9447 0.03033 0.02373 -0.2040 0.2982 0.4205
10.750 1.9575 0.03141 0.02482 -0.2024 0.2944 0.4281
11.000 1.9679 0.03271 0.02614 -0.2006 0.2902 0.4353
11.250 1.9806 0.03386 0.02735 -0.1991 0.2865 0.4440
11.500 1.9954 0.03483 0.02841 -0.1979 0.2829 0.4534
11.750 2.0077 0.03604 0.02971 -0.1965 0.2785 0.4633
12.000 2.0175 0.03750 0.03119 -0.1949 0.2738 0.4734
12.250 2.0258 0.03915 0.03288 -0.1933 0.2690 0.4851
12.500 2.0399 0.04032 0.03417 -0.1923 0.2642 0.4999
12.750 2.0502 0.04186 0.03578 -0.1910 0.2584 0.5172
13.000 2.0547 0.04402 0.03797 -0.1894 0.2523 0.5391
13.250 2.0680 0.04541 0.03951 -0.1885 0.2455 0.5853
13.500 2.0699 0.04740 0.04181 -0.1868 0.2378 1.0000
13.750 2.0771 0.04941 0.04383 -0.1855 0.2295 1.0000
14.000 2.0766 0.05232 0.04671 -0.1840 0.2206 1.0000
14.250 2.0810 0.05473 0.04912 -0.1828 0.2119 1.0000
14.500 2.0790 0.05797 0.05233 -0.1815 0.2040 1.0000
14.750 2.0808 0.06081 0.05518 -0.1804 0.1973 1.0000
15.000 2.0778 0.06431 0.05865 -0.1793 0.1911 1.0000
15.250 2.0802 0.06718 0.06156 -0.1784 0.1866 1.0000
15.500 2.0809 0.07033 0.06473 -0.1776 0.1822 1.0000
15.750 2.0773 0.07410 0.06850 -0.1768 0.1779 1.0000
16.000 2.0805 0.07699 0.07144 -0.1761 0.1744 1.0000
16.250 2.0826 0.08008 0.07460 -0.1756 0.1711 1.0000
16.500 2.0824 0.08350 0.07804 -0.1751 0.1677 1.0000
16.750 2.0783 0.08753 0.08208 -0.1748 0.1641 1.0000
17.000 2.0813 0.09056 0.08518 -0.1744 0.1612 1.0000
17.250 2.0843 0.09361 0.08832 -0.1742 0.1583 1.0000
17.500 2.0843 0.09712 0.09188 -0.1741 0.1552 1.0000
17.750 2.0810 0.10112 0.09590 -0.1741 0.1520 1.0000
18.000 2.0802 0.10476 0.09958 -0.1742 0.1489 1.0000
18.250 2.0842 0.10772 0.10264 -0.1743 0.1461 1.0000
18.500 2.0832 0.11142 0.10642 -0.1746 0.1428 1.0000
18.750 2.0799 0.11545 0.11046 -0.1751 0.1394 1.0000
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