GOE 309 (MVA H.41) AIRFOIL (goe309-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 309 (MVA H.41) AIRFOIL (goe309-il) Reynolds number: 200,000 Max Cl/Cd: 73.43 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe309-il-200000.txt Download as CSV file: xf-goe309-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3639 0.10304 0.09981 -0.0198 1.0000 0.0341
-8.250 -0.3627 0.10032 0.09714 -0.0236 1.0000 0.0343
-8.000 -0.3595 0.09726 0.09411 -0.0275 1.0000 0.0345
-7.750 -0.3522 0.09390 0.09077 -0.0308 1.0000 0.0345
-7.500 -0.3444 0.09050 0.08737 -0.0334 1.0000 0.0346
-7.250 -0.3464 0.08437 0.08132 -0.0329 1.0000 0.0352
-7.000 -0.3428 0.08086 0.07786 -0.0305 1.0000 0.0359
-6.750 -0.3421 0.07834 0.07538 -0.0287 1.0000 0.0366
-6.500 -0.3495 0.07664 0.07374 -0.0262 1.0000 0.0371
-6.250 -0.3360 0.07341 0.07051 -0.0286 0.9960 0.0384
-6.000 -0.3025 0.06861 0.06562 -0.0359 0.9888 0.0411
-5.750 -0.2410 0.06441 0.06101 -0.0507 0.9799 0.0461
-5.500 -0.2241 0.05743 0.05408 -0.0534 0.9736 0.0478
-5.250 -0.1956 0.05395 0.05057 -0.0562 0.9662 0.0501
-5.000 -0.1618 0.05035 0.04682 -0.0604 0.9570 0.0549
-4.750 -0.1261 0.04559 0.04165 -0.0649 0.9442 0.0599
-4.500 -0.1070 0.04312 0.03920 -0.0648 0.9312 0.0624
-4.250 -0.0760 0.04049 0.03607 -0.0660 0.9173 0.0724
-4.000 -0.0598 0.03773 0.03338 -0.0652 0.9038 0.0745
-3.750 -0.0343 0.01906 0.01485 -0.0608 0.8594 0.0810
-3.500 -0.0122 0.01630 0.01173 -0.0605 0.8487 0.0874
-3.250 0.0066 0.03137 0.02643 -0.0630 0.8659 0.0921
-3.000 0.0319 0.02917 0.02381 -0.0623 0.8547 0.1014
-2.750 0.0628 0.02399 0.01772 -0.0606 0.8440 0.0706
-2.500 0.0876 0.02162 0.01502 -0.0597 0.8323 0.0694
-2.250 0.1136 0.01951 0.01254 -0.0588 0.8212 0.0673
-2.000 0.1403 0.01784 0.01048 -0.0579 0.8106 0.0664
-1.750 0.1673 0.01676 0.00909 -0.0572 0.7992 0.0677
-1.500 0.1945 0.01604 0.00812 -0.0566 0.7873 0.0702
-1.250 0.2216 0.01529 0.00717 -0.0559 0.7757 0.0712
-1.000 0.2479 0.01443 0.00622 -0.0553 0.7646 0.0737
-0.750 0.2743 0.01401 0.00575 -0.0548 0.7539 0.0776
-0.500 0.3009 0.01368 0.00534 -0.0542 0.7416 0.0833
-0.250 0.3272 0.01338 0.00507 -0.0538 0.7294 0.0937
0.000 0.3530 0.01294 0.00465 -0.0532 0.7177 0.1152
0.250 0.3783 0.01251 0.00431 -0.0526 0.7063 0.1580
0.500 0.4041 0.01230 0.00417 -0.0522 0.6949 0.1931
0.750 0.4291 0.01195 0.00412 -0.0517 0.6826 0.3011
1.000 0.5072 0.01052 0.00419 -0.0614 0.6679 1.0000
1.250 0.5321 0.01059 0.00411 -0.0607 0.6541 1.0000
1.500 0.5568 0.01066 0.00404 -0.0600 0.6399 1.0000
1.750 0.5813 0.01073 0.00398 -0.0592 0.6251 1.0000
2.000 0.6058 0.01080 0.00392 -0.0584 0.6102 1.0000
2.250 0.6304 0.01090 0.00391 -0.0577 0.5960 1.0000
2.500 0.6551 0.01101 0.00395 -0.0571 0.5833 1.0000
2.750 0.6799 0.01115 0.00403 -0.0565 0.5717 1.0000
3.000 0.7047 0.01131 0.00411 -0.0560 0.5609 1.0000
3.250 0.7294 0.01148 0.00419 -0.0554 0.5508 1.0000
3.500 0.7541 0.01164 0.00432 -0.0548 0.5396 1.0000
3.750 0.7788 0.01181 0.00448 -0.0542 0.5285 1.0000
4.000 0.8034 0.01200 0.00462 -0.0536 0.5178 1.0000
4.250 0.8280 0.01220 0.00477 -0.0530 0.5075 1.0000
4.500 0.8526 0.01239 0.00496 -0.0525 0.4965 1.0000
4.750 0.8773 0.01259 0.00520 -0.0520 0.4856 1.0000
5.000 0.9020 0.01282 0.00541 -0.0514 0.4748 1.0000
5.250 0.9260 0.01300 0.00559 -0.0508 0.4597 1.0000
5.500 0.9491 0.01318 0.00571 -0.0499 0.4389 1.0000
5.750 0.9724 0.01339 0.00592 -0.0492 0.4187 1.0000
6.000 0.9956 0.01362 0.00613 -0.0485 0.3966 1.0000
6.250 1.0185 0.01387 0.00637 -0.0477 0.3714 1.0000
6.500 1.0413 0.01418 0.00665 -0.0470 0.3456 1.0000
6.750 1.0618 0.01466 0.00697 -0.0460 0.3007 1.0000
7.000 1.0795 0.01547 0.00745 -0.0448 0.2483 1.0000
7.250 1.0981 0.01628 0.00805 -0.0436 0.2121 1.0000
7.500 1.1162 0.01716 0.00873 -0.0424 0.1756 1.0000
7.750 1.1342 0.01804 0.00942 -0.0412 0.1385 1.0000
8.000 1.1350 0.02056 0.01114 -0.0380 0.0347 1.0000
8.250 1.1511 0.02157 0.01222 -0.0364 0.0286 1.0000
8.500 1.1686 0.02240 0.01321 -0.0349 0.0272 1.0000
8.750 1.1845 0.02333 0.01432 -0.0333 0.0262 1.0000
9.000 1.1982 0.02438 0.01556 -0.0314 0.0255 1.0000
9.250 1.2090 0.02554 0.01691 -0.0293 0.0250 1.0000
9.500 1.2145 0.02681 0.01834 -0.0264 0.0247 1.0000
9.750 1.2171 0.02833 0.01999 -0.0236 0.0242 1.0000
10.000 1.2175 0.03015 0.02196 -0.0211 0.0235 1.0000
10.250 1.2159 0.03230 0.02421 -0.0190 0.0228 1.0000
10.500 1.2142 0.03469 0.02669 -0.0172 0.0222 1.0000
10.750 1.2148 0.03705 0.02913 -0.0158 0.0221 1.0000
11.000 1.2176 0.03933 0.03148 -0.0145 0.0220 1.0000
11.250 1.2229 0.04145 0.03367 -0.0131 0.0220 1.0000
11.500 1.2311 0.04337 0.03566 -0.0117 0.0222 1.0000
11.750 1.2425 0.04510 0.03748 -0.0103 0.0225 1.0000
12.000 1.2580 0.04665 0.03916 -0.0086 0.0232 1.0000
12.250 1.2755 0.04841 0.04113 -0.0068 0.0245 1.0000
12.500 1.3001 0.05058 0.04348 -0.0049 0.0265 1.0000
12.750 1.3451 0.05295 0.04593 -0.0040 0.0291 1.0000
13.000 1.3431 0.05489 0.04817 -0.0024 0.0300 1.0000
13.250 1.3373 0.05848 0.05228 -0.0008 0.0327 1.0000
13.500 1.2039 0.05522 0.04911 0.0090 0.0294 1.0000
13.750 1.1902 0.05900 0.05318 0.0097 0.0303 1.0000
14.000 1.1713 0.06404 0.05861 0.0103 0.0319 1.0000
14.250 1.1533 0.06930 0.06416 0.0105 0.0331 1.0000
14.500 1.1346 0.07461 0.06971 0.0103 0.0340 1.0000
14.750 1.1152 0.07998 0.07529 0.0098 0.0348 1.0000
15.000 1.0921 0.08535 0.08085 0.0087 0.0351 1.0000
15.250 1.0680 0.09079 0.08647 0.0074 0.0357 1.0000
15.500 1.0431 0.09591 0.09173 0.0071 0.0367 1.0000
15.750 1.0111 0.10083 0.09684 0.0045 0.0366 1.0000
16.000 1.0067 0.10366 0.09985 0.0033 0.0383 1.0000
16.250 0.9772 0.10960 0.10594 -0.0002 0.0383 1.0000
16.500 0.9459 0.11636 0.11286 -0.0046 0.0384 1.0000
16.750 0.8928 0.12676 0.12340 -0.0124 0.0361 1.0000
17.000 0.8566 0.13615 0.13292 -0.0193 0.0348 1.0000
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