GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Reynolds number: 200,000 Max Cl/Cd: 66.64 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe165-il-200000-n5.txt Download as CSV file: xf-goe165-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 165 (MVA MK.11) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2997 0.10858 0.10532 -0.0346 1.0000 0.0264
-9.000 -0.3040 0.10509 0.10190 -0.0357 1.0000 0.0266
-8.750 -0.3083 0.10175 0.09863 -0.0363 1.0000 0.0267
-8.500 -0.3125 0.09862 0.09556 -0.0363 1.0000 0.0268
-8.250 -0.3031 0.09573 0.09270 -0.0351 0.9991 0.0276
-8.000 -0.2863 0.09250 0.08947 -0.0378 0.9965 0.0284
-7.750 -0.2712 0.08857 0.08554 -0.0418 0.9929 0.0292
-7.500 -0.2617 0.07976 0.07673 -0.0492 0.9871 0.0173
-7.250 -0.2524 0.07495 0.07195 -0.0537 0.9794 0.0160
-7.000 -0.2381 0.06817 0.06519 -0.0615 0.9696 0.0149
-6.750 -0.2255 0.05658 0.05357 -0.0755 0.9571 0.0136
-6.250 -0.1312 0.03194 0.02736 -0.1220 0.9307 0.0112
-6.000 -0.0941 0.02841 0.02337 -0.1270 0.9196 0.0112
-5.750 -0.0526 0.02497 0.01946 -0.1319 0.9111 0.0112
-5.500 -0.0133 0.02188 0.01593 -0.1356 0.9009 0.0116
-5.250 0.0270 0.01982 0.01367 -0.1391 0.8896 0.0129
-5.000 0.0719 0.01821 0.01184 -0.1429 0.8772 0.0139
-4.750 0.1188 0.01671 0.01014 -0.1469 0.8613 0.0144
-4.500 0.1669 0.01549 0.00871 -0.1512 0.8396 0.0151
-4.250 0.2119 0.01455 0.00750 -0.1549 0.8116 0.0160
-4.000 0.2506 0.01397 0.00661 -0.1572 0.7833 0.0178
-3.750 0.2849 0.01343 0.00570 -0.1586 0.7586 0.0203
-3.500 0.3158 0.01314 0.00514 -0.1591 0.7381 0.0234
-3.250 0.3455 0.01291 0.00480 -0.1594 0.7215 0.0407
-3.000 0.3746 0.01268 0.00441 -0.1597 0.7067 0.0631
-2.750 0.4043 0.01197 0.00399 -0.1607 0.6938 0.2030
-2.500 0.4322 0.01184 0.00406 -0.1608 0.6813 0.2854
-2.250 0.4595 0.01201 0.00417 -0.1605 0.6690 0.3173
-1.750 0.5141 0.01231 0.00423 -0.1598 0.6465 0.3450
-1.500 0.5415 0.01240 0.00418 -0.1596 0.6356 0.3519
-1.250 0.5685 0.01254 0.00422 -0.1592 0.6249 0.3574
-1.000 0.5956 0.01264 0.00420 -0.1589 0.6133 0.3643
-0.750 0.6223 0.01279 0.00430 -0.1585 0.6008 0.3711
-0.500 0.6489 0.01297 0.00439 -0.1581 0.5862 0.3815
-0.250 0.6747 0.01318 0.00456 -0.1574 0.5683 0.3894
0.000 0.7007 0.01330 0.00455 -0.1569 0.5441 0.3955
0.250 0.7250 0.01347 0.00457 -0.1561 0.5051 0.3978
0.500 0.7471 0.01380 0.00461 -0.1549 0.4586 0.4004
0.750 0.7702 0.01415 0.00474 -0.1539 0.4290 0.4036
1.000 0.7942 0.01448 0.00489 -0.1532 0.4076 0.4077
1.250 0.8184 0.01482 0.00507 -0.1525 0.3898 0.4121
1.500 0.8428 0.01514 0.00532 -0.1518 0.3744 0.4166
1.750 0.8676 0.01543 0.00552 -0.1512 0.3610 0.4222
2.000 0.8928 0.01568 0.00569 -0.1507 0.3506 0.4266
2.250 0.9181 0.01589 0.00590 -0.1502 0.3424 0.4296
2.500 0.9435 0.01609 0.00609 -0.1498 0.3356 0.4331
2.750 0.9690 0.01630 0.00626 -0.1493 0.3279 0.4366
3.000 0.9944 0.01650 0.00644 -0.1489 0.3202 0.4395
3.250 1.0197 0.01668 0.00662 -0.1484 0.3127 0.4416
3.500 1.0447 0.01688 0.00683 -0.1479 0.3063 0.4434
3.750 1.0701 0.01705 0.00705 -0.1475 0.2993 0.4457
4.000 1.0946 0.01729 0.00729 -0.1469 0.2932 0.4484
4.250 1.1201 0.01745 0.00751 -0.1465 0.2878 0.4513
4.500 1.1450 0.01765 0.00776 -0.1460 0.2821 0.4540
4.750 1.1695 0.01787 0.00801 -0.1454 0.2762 0.4563
5.000 1.1943 0.01805 0.00828 -0.1449 0.2694 0.4584
5.250 1.2182 0.01829 0.00855 -0.1442 0.2594 0.4608
5.500 1.2408 0.01862 0.00884 -0.1434 0.2365 0.4635
5.750 1.2575 0.01946 0.00931 -0.1418 0.1747 0.4664
6.000 1.2666 0.02116 0.01050 -0.1391 0.1076 0.4691
6.250 1.2825 0.02215 0.01134 -0.1373 0.0621 0.4717
6.500 1.3004 0.02288 0.01209 -0.1358 0.0530 0.4743
6.750 1.3202 0.02340 0.01278 -0.1344 0.0470 0.4772
7.000 1.3393 0.02395 0.01343 -0.1330 0.0398 0.4803
7.250 1.3547 0.02478 0.01421 -0.1311 0.0167 0.4834
7.500 1.3702 0.02550 0.01508 -0.1290 0.0146 0.4864
7.750 1.3832 0.02627 0.01603 -0.1266 0.0130 0.4892
8.000 1.3946 0.02721 0.01716 -0.1239 0.0113 0.4924
8.250 1.4069 0.02809 0.01821 -0.1215 0.0106 0.4963
8.500 1.4176 0.02909 0.01937 -0.1190 0.0102 0.5002
8.750 1.4263 0.03021 0.02069 -0.1163 0.0098 0.5038
9.000 1.4328 0.03149 0.02221 -0.1135 0.0094 0.5078
9.250 1.4371 0.03298 0.02388 -0.1106 0.0090 0.5120
9.500 1.4389 0.03470 0.02579 -0.1078 0.0086 0.5158
9.750 1.4374 0.03678 0.02805 -0.1050 0.0082 0.5195
10.000 1.4319 0.03936 0.03081 -0.1024 0.0079 0.5233
10.250 1.4222 0.04259 0.03421 -0.1002 0.0076 0.5271
10.500 1.4075 0.04669 0.03848 -0.0986 0.0074 0.5303
10.750 1.4064 0.04965 0.04161 -0.0978 0.0073 0.5355
11.000 1.4016 0.05323 0.04535 -0.0974 0.0071 0.5410
11.250 1.3955 0.05709 0.04938 -0.0972 0.0070 0.5472
11.500 1.3889 0.06112 0.05357 -0.0972 0.0070 0.5549
11.750 1.3821 0.06526 0.05786 -0.0972 0.0069 0.5646
12.000 1.3751 0.06945 0.06222 -0.0974 0.0068 0.5794
12.250 1.3694 0.07354 0.06658 -0.0977 0.0067 0.6405
12.500 1.3601 0.07707 0.07052 -0.0971 0.0067 1.0000
12.750 1.3553 0.08107 0.07461 -0.0972 0.0066 1.0000
13.000 1.3520 0.08486 0.07849 -0.0973 0.0065 1.0000
13.250 1.3502 0.08842 0.08213 -0.0972 0.0064 1.0000
13.500 1.3499 0.09174 0.08552 -0.0970 0.0063 1.0000
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Polar data table (+)
Polar graphs
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