E. Bambino (ebambino7-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E. Bambino (ebambino7-il) Reynolds number: 50,000 Max Cl/Cd: 26.32 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ebambino7-il-50000.txt Download as CSV file: xf-ebambino7-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: E. Bambino
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.500 -0.6067 0.10333 0.09754 0.0204 1.0000 0.1541
-6.250 -0.5982 0.09864 0.09291 0.0207 1.0000 0.1612
-6.000 -0.6039 0.09604 0.09031 0.0139 1.0000 0.1688
-5.750 -0.5927 0.09118 0.08552 0.0155 1.0000 0.1807
-5.500 -0.5852 0.08700 0.08137 0.0149 1.0000 0.1929
-5.250 -0.5809 0.08336 0.07774 0.0126 1.0000 0.2084
-5.000 -0.5731 0.07911 0.07354 0.0125 1.0000 0.2260
-4.750 -0.5673 0.07564 0.07009 0.0117 1.0000 0.2516
-4.500 -0.5566 0.07155 0.06612 0.0153 1.0000 0.2828
-4.000 -0.2343 0.05218 0.04645 0.0328 1.0000 1.0000
-3.750 -0.2216 0.04929 0.04360 0.0310 1.0000 1.0000
-3.500 -0.2653 0.05063 0.04512 0.0424 1.0000 0.9607
-3.250 -0.3203 0.05180 0.04646 0.0531 1.0000 0.8908
-3.000 -0.3686 0.05149 0.04634 0.0589 1.0000 0.8218
-2.750 -0.4093 0.04967 0.04471 0.0603 1.0000 0.7558
-2.500 -0.4469 0.04694 0.04220 0.0599 1.0000 0.7052
-2.250 -0.3313 0.02261 0.01602 -0.0056 1.0000 0.2594
-2.000 -0.2949 0.03456 0.02607 -0.0072 1.0000 0.1648
-1.750 -0.2602 0.03194 0.02284 -0.0068 1.0000 0.1351
-1.500 -0.2260 0.03015 0.02027 -0.0057 1.0000 0.1144
-1.250 -0.1965 0.02750 0.01744 -0.0051 1.0000 0.1058
-1.000 -0.1658 0.02584 0.01533 -0.0040 1.0000 0.0999
-0.750 -0.1361 0.02392 0.01326 -0.0032 1.0000 0.0988
-0.500 -0.1042 0.02237 0.01150 -0.0024 1.0000 0.1009
-0.250 -0.0752 0.02077 0.00994 -0.0015 1.0000 0.1095
0.000 -0.0516 0.01945 0.00872 -0.0003 1.0000 0.1376
0.250 -0.0315 0.01730 0.00735 0.0013 1.0000 0.2408
0.500 0.0488 0.01514 0.00628 -0.0054 1.0000 1.0000
0.750 0.0684 0.01516 0.00610 -0.0041 1.0000 1.0000
1.000 0.0862 0.01523 0.00603 -0.0027 1.0000 1.0000
1.250 0.1017 0.01536 0.00605 -0.0009 1.0000 1.0000
1.500 0.1155 0.01555 0.00618 0.0010 1.0000 1.0000
1.750 0.1287 0.01582 0.00632 0.0028 1.0000 1.0000
2.000 0.1423 0.01617 0.00660 0.0044 1.0000 1.0000
2.250 0.2096 0.01632 0.00676 -0.0038 0.9715 1.0000
2.500 0.2767 0.01626 0.00677 -0.0106 0.9221 1.0000
2.750 0.3130 0.01619 0.00672 -0.0103 0.8536 1.0000
3.000 0.3315 0.01618 0.00644 -0.0057 0.7649 1.0000
3.250 0.3454 0.01646 0.00622 -0.0007 0.6616 1.0000
3.500 0.3589 0.01724 0.00602 0.0036 0.4122 1.0000
3.750 0.3771 0.01948 0.00673 0.0046 0.2120 1.0000
4.000 0.3999 0.02090 0.00768 0.0050 0.1785 1.0000
4.250 0.4238 0.02201 0.00868 0.0056 0.1655 1.0000
4.500 0.4483 0.02304 0.00974 0.0062 0.1581 1.0000
4.750 0.4736 0.02392 0.01069 0.0068 0.1526 1.0000
5.000 0.4987 0.02490 0.01164 0.0075 0.1488 1.0000
5.250 0.5244 0.02594 0.01269 0.0080 0.1464 1.0000
5.500 0.5506 0.02686 0.01380 0.0084 0.1445 1.0000
5.750 0.5755 0.02752 0.01458 0.0086 0.1375 1.0000
6.000 0.5987 0.02760 0.01476 0.0085 0.1242 1.0000
6.250 0.6231 0.02818 0.01548 0.0087 0.1205 1.0000
6.500 0.6475 0.02808 0.01566 0.0086 0.1111 1.0000
6.750 0.6721 0.02862 0.01627 0.0088 0.1091 1.0000
7.000 0.6968 0.02901 0.01689 0.0089 0.1043 1.0000
7.250 0.7208 0.02885 0.01683 0.0088 0.0973 1.0000
7.500 0.7458 0.02966 0.01790 0.0091 0.0974 1.0000
7.750 0.7708 0.03048 0.01921 0.0095 0.0975 1.0000
8.000 0.7958 0.03134 0.02040 0.0098 0.0972 1.0000
8.250 0.8206 0.03227 0.02168 0.0102 0.0967 1.0000
8.500 0.8449 0.03322 0.02299 0.0106 0.0941 1.0000
8.750 0.8672 0.03295 0.02277 0.0107 0.0833 1.0000
9.000 0.8893 0.03418 0.02436 0.0112 0.0757 1.0000
9.250 0.9095 0.03631 0.02666 0.0119 0.0709 1.0000
9.500 0.9277 0.03985 0.03085 0.0128 0.0659 1.0000
9.750 0.9423 0.04375 0.03501 0.0136 0.0612 1.0000
10.000 0.9506 0.04914 0.04090 0.0142 0.0589 1.0000
10.250 0.9510 0.05493 0.04741 0.0145 0.0581 1.0000
10.500 0.9448 0.06086 0.05385 0.0142 0.0579 1.0000
10.750 0.9333 0.06672 0.06006 0.0133 0.0581 1.0000
11.000 0.9180 0.07248 0.06604 0.0117 0.0585 1.0000
11.250 0.8999 0.07801 0.07166 0.0095 0.0589 1.0000
11.500 0.8839 0.08441 0.07811 0.0055 0.0594 1.0000
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Polar data table (+)
Polar graphs
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