MH33 (mh33-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH33 (mh33-il) Reynolds number: 200,000 Max Cl/Cd: 51.24 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh33-il-200000-n5.txt Download as CSV file: xf-mh33-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH33
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 -0.4560 0.08701 0.08366 -0.0137 1.0000 0.0117
-9.000 -0.4566 0.08285 0.07952 -0.0153 1.0000 0.0136
-8.750 -0.4610 0.07766 0.07437 -0.0170 1.0000 0.0124
-7.250 -0.5607 0.05150 0.04778 -0.0332 1.0000 0.0090
-7.000 -0.5631 0.04636 0.04238 -0.0328 1.0000 0.0092
-6.750 -0.5591 0.04230 0.03805 -0.0317 1.0000 0.0091
-6.500 -0.5565 0.03774 0.03313 -0.0302 1.0000 0.0094
-6.250 -0.5461 0.03451 0.02955 -0.0285 1.0000 0.0093
-5.250 -0.4858 0.02455 0.01814 -0.0212 1.0000 0.0088
-5.000 -0.4676 0.02224 0.01546 -0.0195 1.0000 0.0087
-4.750 -0.4478 0.02026 0.01316 -0.0180 1.0000 0.0087
-4.500 -0.4269 0.01868 0.01127 -0.0165 1.0000 0.0087
-4.250 -0.4057 0.01726 0.00965 -0.0151 1.0000 0.0088
-4.000 -0.3848 0.01590 0.00817 -0.0137 1.0000 0.0090
-3.750 -0.3640 0.01456 0.00666 -0.0123 1.0000 0.0096
-3.500 -0.3421 0.01374 0.00570 -0.0112 1.0000 0.0104
-3.250 -0.3153 0.01309 0.00491 -0.0110 0.9988 0.0124
-3.000 -0.2807 0.01240 0.00417 -0.0123 0.9950 0.0273
-2.750 -0.2506 0.01108 0.00380 -0.0138 0.9911 0.1955
-2.500 -0.2178 0.01049 0.00351 -0.0153 0.9864 0.2994
-2.250 -0.1837 0.00996 0.00336 -0.0170 0.9822 0.4110
-2.000 -0.1534 0.00945 0.00322 -0.0177 0.9764 0.5196
-1.750 -0.1218 0.00896 0.00314 -0.0185 0.9709 0.6350
-1.250 -0.0577 0.00839 0.00322 -0.0187 0.9604 0.8661
-1.000 -0.0109 0.00841 0.00322 -0.0222 0.9575 0.9286
-0.750 0.0367 0.00841 0.00315 -0.0261 0.9538 0.9568
-0.500 0.0827 0.00837 0.00303 -0.0298 0.9471 0.9755
-0.250 0.1335 0.00830 0.00291 -0.0345 0.9417 0.9870
0.000 0.1792 0.00821 0.00278 -0.0383 0.9312 0.9971
0.250 0.2169 0.00811 0.00265 -0.0403 0.9168 1.0000
0.500 0.2475 0.00801 0.00254 -0.0407 0.8972 1.0000
0.750 0.2777 0.00792 0.00240 -0.0409 0.8734 1.0000
1.000 0.3057 0.00786 0.00228 -0.0406 0.8428 1.0000
1.250 0.3323 0.00785 0.00217 -0.0399 0.8062 1.0000
1.500 0.3565 0.00793 0.00210 -0.0388 0.7637 1.0000
1.750 0.3793 0.00808 0.00210 -0.0374 0.7175 1.0000
2.000 0.4012 0.00830 0.00212 -0.0360 0.6685 1.0000
2.250 0.4226 0.00858 0.00219 -0.0345 0.6177 1.0000
2.500 0.4438 0.00889 0.00229 -0.0330 0.5660 1.0000
2.750 0.4650 0.00922 0.00242 -0.0316 0.5148 1.0000
3.000 0.4863 0.00958 0.00263 -0.0303 0.4641 1.0000
3.250 0.5077 0.00996 0.00283 -0.0291 0.4160 1.0000
3.500 0.5295 0.01034 0.00305 -0.0280 0.3695 1.0000
3.750 0.5513 0.01076 0.00330 -0.0269 0.3232 1.0000
4.000 0.5734 0.01119 0.00358 -0.0259 0.2787 1.0000
4.250 0.5956 0.01164 0.00394 -0.0250 0.2364 1.0000
4.500 0.6182 0.01211 0.00429 -0.0241 0.1995 1.0000
4.750 0.6409 0.01258 0.00467 -0.0233 0.1650 1.0000
5.000 0.6634 0.01311 0.00509 -0.0225 0.1329 1.0000
5.250 0.6862 0.01364 0.00556 -0.0217 0.1059 1.0000
5.500 0.7086 0.01425 0.00607 -0.0209 0.0777 1.0000
5.750 0.7309 0.01490 0.00663 -0.0201 0.0558 1.0000
6.000 0.7534 0.01555 0.00730 -0.0192 0.0416 1.0000
6.250 0.7752 0.01635 0.00821 -0.0182 0.0319 1.0000
6.500 0.7971 0.01717 0.00917 -0.0172 0.0261 1.0000
6.750 0.8165 0.01839 0.01048 -0.0158 0.0218 1.0000
7.000 0.8387 0.01916 0.01143 -0.0148 0.0181 1.0000
7.250 0.8579 0.02041 0.01276 -0.0137 0.0135 1.0000
7.500 0.8795 0.02130 0.01382 -0.0127 0.0101 1.0000
7.750 0.8987 0.02246 0.01505 -0.0118 0.0066 1.0000
8.000 0.9185 0.02369 0.01652 -0.0106 0.0053 1.0000
8.250 0.9355 0.02546 0.01855 -0.0090 0.0046 1.0000
8.500 0.9517 0.02731 0.02068 -0.0075 0.0042 1.0000
8.750 0.9667 0.02916 0.02279 -0.0060 0.0037 1.0000
9.000 0.9789 0.03135 0.02536 -0.0044 0.0035 1.0000
9.250 0.9858 0.03423 0.02862 -0.0023 0.0033 1.0000
9.500 0.9898 0.03724 0.03202 -0.0002 0.0033 1.0000
9.750 0.9825 0.04129 0.03651 0.0026 0.0032 1.0000
10.000 0.9765 0.04432 0.03984 0.0051 0.0032 1.0000
10.250 0.9576 0.04808 0.04389 0.0079 0.0031 1.0000
10.500 0.9423 0.05181 0.04784 0.0088 0.0031 1.0000
10.750 0.9238 0.05669 0.05294 0.0073 0.0031 1.0000
11.000 0.9086 0.06253 0.05896 0.0033 0.0032 1.0000
11.250 0.8919 0.07084 0.06744 -0.0036 0.0032 1.0000
11.500 0.8768 0.08110 0.07786 -0.0111 0.0034 1.0000
11.750 0.8228 0.10226 0.09899 -0.0221 0.0040 1.0000
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Polar data table (+)
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