GOE 309 (MVA H.41) AIRFOIL (goe309-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 309 (MVA H.41) AIRFOIL (goe309-il) Reynolds number: 500,000 Max Cl/Cd: 90.61 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe309-il-500000-n5.txt Download as CSV file: xf-goe309-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 309 (MVA H.41) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3739 0.10167 0.09961 -0.0129 1.0000 0.0060
-8.750 -0.3699 0.09787 0.09583 -0.0148 1.0000 0.0060
-8.250 -0.3645 0.08981 0.08781 -0.0193 1.0000 0.0065
-8.000 -0.3573 0.08473 0.08273 -0.0244 0.9632 0.0068
-7.750 -0.3554 0.08054 0.07850 -0.0278 0.9338 0.0068
-7.500 -0.3510 0.07619 0.07409 -0.0310 0.9032 0.0068
-7.250 -0.3450 0.07144 0.06921 -0.0344 0.8720 0.0069
-7.000 -0.3364 0.06588 0.06351 -0.0385 0.8462 0.0070
-6.750 -0.3252 0.05944 0.05689 -0.0431 0.8259 0.0072
-6.250 -0.3255 0.01798 0.01313 -0.0547 0.8051 0.0088
-6.000 -0.3011 0.01625 0.01098 -0.0543 0.7922 0.0097
-5.500 -0.2489 0.01437 0.00861 -0.0537 0.7691 0.0120
-5.250 -0.2214 0.01415 0.00831 -0.0536 0.7590 0.0133
-5.000 -0.1942 0.01373 0.00769 -0.0535 0.7492 0.0149
-4.750 -0.1667 0.01349 0.00736 -0.0534 0.7396 0.0164
-4.500 -0.1383 0.01383 0.00772 -0.0535 0.7310 0.0182
-4.250 -0.1106 0.01375 0.00755 -0.0535 0.7222 0.0205
-4.000 -0.0827 0.01352 0.00718 -0.0534 0.7134 0.0226
-3.750 -0.0546 0.01359 0.00715 -0.0534 0.7050 0.0238
-3.500 -0.0275 0.01280 0.00616 -0.0533 0.6969 0.0255
-3.250 0.0000 0.01245 0.00575 -0.0533 0.6889 0.0275
-3.000 0.0277 0.01225 0.00545 -0.0533 0.6800 0.0291
-2.750 0.0555 0.01196 0.00506 -0.0533 0.6712 0.0306
-2.500 0.0832 0.01166 0.00464 -0.0532 0.6626 0.0318
-2.250 0.1109 0.01129 0.00417 -0.0531 0.6537 0.0323
-2.000 0.1385 0.01097 0.00375 -0.0530 0.6447 0.0327
-1.750 0.1660 0.01072 0.00341 -0.0529 0.6347 0.0332
-1.500 0.1937 0.01049 0.00311 -0.0528 0.6241 0.0338
-1.250 0.2212 0.01025 0.00279 -0.0527 0.6140 0.0339
-1.000 0.2487 0.01007 0.00253 -0.0526 0.6037 0.0341
-0.750 0.2763 0.00992 0.00231 -0.0526 0.5922 0.0344
-0.500 0.3040 0.00981 0.00212 -0.0525 0.5803 0.0348
-0.250 0.3317 0.00975 0.00198 -0.0525 0.5675 0.0353
0.000 0.3592 0.00968 0.00182 -0.0524 0.5526 0.0380
0.250 0.3866 0.00964 0.00173 -0.0524 0.5363 0.0439
0.500 0.4139 0.00960 0.00170 -0.0524 0.5205 0.0622
0.750 0.4414 0.00962 0.00173 -0.0524 0.5061 0.0902
1.000 0.4690 0.00968 0.00175 -0.0524 0.4923 0.1023
1.250 0.4965 0.00973 0.00176 -0.0524 0.4782 0.1107
1.750 0.5513 0.00985 0.00182 -0.0525 0.4515 0.1296
2.000 0.5782 0.00972 0.00193 -0.0526 0.4420 0.2297
2.250 0.6039 0.00932 0.00201 -0.0526 0.4326 0.4549
2.500 0.6186 0.00819 0.00217 -0.0494 0.4257 0.9525
2.750 0.6525 0.00831 0.00226 -0.0507 0.4172 0.9745
3.000 0.6893 0.00844 0.00236 -0.0528 0.4091 0.9873
3.250 0.7248 0.00860 0.00247 -0.0547 0.4006 0.9942
3.500 0.7614 0.00873 0.00257 -0.0569 0.3920 0.9982
3.750 0.7914 0.00887 0.00269 -0.0575 0.3837 1.0000
4.000 0.8160 0.00903 0.00280 -0.0570 0.3717 1.0000
4.250 0.8400 0.00927 0.00293 -0.0565 0.3461 1.0000
4.500 0.8638 0.00954 0.00309 -0.0559 0.3208 1.0000
4.750 0.8866 0.00994 0.00332 -0.0552 0.2852 1.0000
5.000 0.9078 0.01056 0.00366 -0.0544 0.2349 1.0000
5.250 0.9296 0.01114 0.00402 -0.0536 0.1991 1.0000
5.500 0.9516 0.01169 0.00439 -0.0529 0.1680 1.0000
5.750 0.9739 0.01223 0.00478 -0.0523 0.1396 1.0000
6.000 0.9853 0.01404 0.00595 -0.0502 0.0198 1.0000
6.250 1.0089 0.01442 0.00635 -0.0496 0.0150 1.0000
6.500 1.0325 0.01480 0.00682 -0.0491 0.0123 1.0000
6.750 1.0561 0.01517 0.00726 -0.0485 0.0111 1.0000
7.000 1.0790 0.01560 0.00777 -0.0479 0.0100 1.0000
7.250 1.1011 0.01612 0.00837 -0.0472 0.0091 1.0000
7.500 1.1211 0.01683 0.00919 -0.0462 0.0082 1.0000
7.750 1.1420 0.01742 0.00985 -0.0453 0.0075 1.0000
8.000 1.1624 0.01803 0.01055 -0.0444 0.0069 1.0000
8.250 1.1813 0.01875 0.01135 -0.0433 0.0064 1.0000
8.500 1.1991 0.01952 0.01219 -0.0420 0.0061 1.0000
8.750 1.2152 0.02037 0.01311 -0.0406 0.0057 1.0000
9.000 1.2272 0.02148 0.01431 -0.0387 0.0055 1.0000
9.250 1.2332 0.02284 0.01577 -0.0358 0.0053 1.0000
9.500 1.2419 0.02382 0.01685 -0.0334 0.0051 1.0000
9.750 1.2499 0.02494 0.01806 -0.0311 0.0048 1.0000
10.000 1.2573 0.02618 0.01940 -0.0291 0.0045 1.0000
10.250 1.2636 0.02761 0.02096 -0.0273 0.0043 1.0000
10.500 1.2679 0.02933 0.02277 -0.0256 0.0042 1.0000
10.750 1.2720 0.03120 0.02474 -0.0243 0.0040 1.0000
11.000 1.2759 0.03320 0.02684 -0.0232 0.0039 1.0000
11.250 1.2791 0.03540 0.02912 -0.0224 0.0038 1.0000
11.500 1.2819 0.03771 0.03153 -0.0218 0.0037 1.0000
11.750 1.2833 0.04025 0.03415 -0.0212 0.0036 1.0000
12.000 1.2823 0.04309 0.03707 -0.0207 0.0035 1.0000
12.250 1.2787 0.04622 0.04029 -0.0199 0.0035 1.0000
12.500 1.2789 0.04901 0.04319 -0.0193 0.0034 1.0000
12.750 1.2795 0.05179 0.04609 -0.0187 0.0034 1.0000
13.000 1.2799 0.05462 0.04905 -0.0179 0.0033 1.0000
13.250 1.2802 0.05748 0.05204 -0.0171 0.0032 1.0000
13.500 1.2805 0.06042 0.05511 -0.0162 0.0032 1.0000
13.750 1.2803 0.06353 0.05836 -0.0155 0.0031 1.0000
14.000 1.2787 0.06690 0.06188 -0.0151 0.0031 1.0000
14.250 1.2754 0.07061 0.06575 -0.0151 0.0030 1.0000
14.500 1.2706 0.07464 0.06995 -0.0155 0.0030 1.0000
14.750 1.2643 0.07896 0.07447 -0.0163 0.0029 1.0000
15.000 1.2568 0.08360 0.07927 -0.0176 0.0028 1.0000
15.250 1.2483 0.08856 0.08439 -0.0191 0.0028 1.0000
15.500 1.2393 0.09377 0.08976 -0.0211 0.0027 1.0000
15.750 1.2293 0.09926 0.09540 -0.0234 0.0027 1.0000
16.000 1.2188 0.10505 0.10134 -0.0259 0.0026 1.0000
16.250 1.2079 0.11110 0.10753 -0.0288 0.0026 1.0000
16.500 1.1967 0.11741 0.11399 -0.0320 0.0026 1.0000
16.750 1.1843 0.12416 0.12088 -0.0355 0.0026 1.0000
17.000 1.1724 0.13102 0.12788 -0.0392 0.0026 1.0000
17.250 1.1600 0.13831 0.13531 -0.0434 0.0026 1.0000
17.500 1.1477 0.14588 0.14302 -0.0478 0.0026 1.0000
17.750 1.1354 0.15383 0.15110 -0.0526 0.0026 1.0000
18.000 1.1223 0.16232 0.15972 -0.0578 0.0026 1.0000
18.250 1.1096 0.17116 0.16868 -0.0632 0.0026 1.0000
18.500 1.0969 0.18050 0.17814 -0.0690 0.0026 1.0000
18.750 1.0838 0.19064 0.18838 -0.0752 0.0027 1.0000
19.000 1.0702 0.20198 0.19978 -0.0818 0.0028 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 309 (MVA H.41) AIRFOIL (goe309-il)