FX 79-L-100 (fx79l100-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 79-L-100 (fx79l100-il) Reynolds number: 50,000 Max Cl/Cd: 27.69 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx79l100-il-50000.txt Download as CSV file: xf-fx79l100-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: FX 79-L-100
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.7349 0.07979 0.07296 -0.0126 1.0000 0.1651
-8.750 -0.7558 0.07204 0.06509 -0.0158 1.0000 0.1515
-8.500 -0.7632 0.06627 0.05913 -0.0168 1.0000 0.1450
-8.250 -0.7940 0.05954 0.05164 -0.0175 1.0000 0.1352
-8.000 -0.7848 0.05483 0.04667 -0.0169 1.0000 0.1335
-7.750 -0.7762 0.05039 0.04189 -0.0161 1.0000 0.1321
-7.500 -0.7670 0.04638 0.03739 -0.0149 1.0000 0.1322
-7.250 -0.7574 0.04311 0.03337 -0.0132 1.0000 0.1349
-7.000 -0.7365 0.03980 0.03012 -0.0126 1.0000 0.1402
-6.750 -0.7173 0.03679 0.02669 -0.0114 1.0000 0.1440
-6.500 -0.6977 0.03418 0.02362 -0.0101 1.0000 0.1512
-6.250 -0.6745 0.03193 0.02122 -0.0091 1.0000 0.1613
-6.000 -0.6493 0.02959 0.01880 -0.0083 1.0000 0.1722
-5.750 -0.6252 0.02768 0.01679 -0.0073 1.0000 0.1904
-5.500 -0.5996 0.02568 0.01494 -0.0064 1.0000 0.2123
-5.250 -0.5774 0.02384 0.01337 -0.0050 1.0000 0.2478
-5.000 -0.5599 0.02169 0.01186 -0.0030 1.0000 0.3134
-4.750 -0.5565 0.02009 0.01191 0.0030 1.0000 0.4946
-4.500 -0.5497 0.02100 0.01315 0.0109 1.0000 0.6159
-4.250 -0.5350 0.02185 0.01397 0.0172 1.0000 0.6764
-4.000 -0.5168 0.02252 0.01458 0.0227 1.0000 0.7225
-3.750 -0.4976 0.02296 0.01491 0.0277 1.0000 0.7640
-3.500 -0.4616 0.02380 0.01554 0.0310 1.0000 0.8057
-3.250 -0.4017 0.02455 0.01595 0.0295 1.0000 0.8467
-3.000 -0.3278 0.02473 0.01569 0.0231 1.0000 0.8798
-2.750 -0.2666 0.02429 0.01496 0.0171 1.0000 0.9043
-2.500 -0.2099 0.02363 0.01406 0.0111 1.0000 0.9246
-2.250 -0.1623 0.02290 0.01318 0.0063 1.0000 0.9430
-2.000 -0.1153 0.02214 0.01230 0.0014 1.0000 0.9601
-1.750 -0.0618 0.02125 0.01132 -0.0050 1.0000 0.9755
-1.500 -0.0110 0.02039 0.01040 -0.0112 1.0000 0.9907
-1.250 0.0279 0.01966 0.00967 -0.0154 1.0000 1.0000
-1.000 0.0398 0.01926 0.00934 -0.0145 1.0000 1.0000
-0.750 0.0486 0.01893 0.00911 -0.0133 1.0000 1.0000
-0.500 0.0501 0.01873 0.00903 -0.0111 1.0000 1.0000
-0.250 0.0351 0.01877 0.00916 -0.0068 1.0000 1.0000
0.000 0.0000 0.01887 0.00929 0.0000 1.0000 1.0000
0.250 -0.0351 0.01876 0.00916 0.0068 1.0000 1.0000
0.500 -0.0502 0.01873 0.00903 0.0111 1.0000 1.0000
0.750 -0.0487 0.01893 0.00911 0.0132 1.0000 1.0000
1.000 -0.0399 0.01925 0.00933 0.0145 1.0000 1.0000
1.250 -0.0280 0.01966 0.00967 0.0153 1.0000 1.0000
1.500 0.0107 0.02039 0.01040 0.0112 0.9907 1.0000
1.750 0.0616 0.02124 0.01131 0.0050 0.9755 1.0000
2.000 0.1143 0.02213 0.01229 -0.0012 0.9603 1.0000
2.250 0.1620 0.02290 0.01318 -0.0063 0.9433 1.0000
2.500 0.2097 0.02363 0.01405 -0.0111 0.9247 1.0000
2.750 0.2660 0.02429 0.01496 -0.0170 0.9044 1.0000
3.000 0.3267 0.02474 0.01570 -0.0230 0.8805 1.0000
3.250 0.4002 0.02459 0.01597 -0.0293 0.8474 1.0000
3.500 0.4615 0.02378 0.01555 -0.0310 0.8056 1.0000
3.750 0.4978 0.02295 0.01490 -0.0277 0.7643 1.0000
4.000 0.5167 0.02250 0.01456 -0.0227 0.7225 1.0000
4.250 0.5349 0.02186 0.01399 -0.0173 0.6768 1.0000
4.500 0.5496 0.02098 0.01310 -0.0109 0.6157 1.0000
4.750 0.5566 0.02010 0.01193 -0.0032 0.4963 1.0000
5.000 0.5600 0.02168 0.01187 0.0029 0.3140 1.0000
5.250 0.5774 0.02384 0.01337 0.0050 0.2481 1.0000
5.500 0.5994 0.02567 0.01492 0.0064 0.2122 1.0000
5.750 0.6253 0.02767 0.01678 0.0073 0.1909 1.0000
6.000 0.6494 0.02958 0.01879 0.0083 0.1728 1.0000
6.250 0.6746 0.03191 0.02118 0.0091 0.1617 1.0000
6.500 0.6976 0.03414 0.02358 0.0101 0.1512 1.0000
6.750 0.7173 0.03678 0.02668 0.0113 0.1440 1.0000
7.000 0.7365 0.03981 0.03013 0.0126 0.1400 1.0000
7.250 0.7571 0.04313 0.03341 0.0132 0.1348 1.0000
7.500 0.7670 0.04640 0.03740 0.0149 0.1322 1.0000
7.750 0.7758 0.05044 0.04195 0.0161 0.1320 1.0000
8.000 0.7840 0.05491 0.04677 0.0170 0.1333 1.0000
8.250 0.7857 0.05962 0.05194 0.0176 0.1365 1.0000
8.500 0.7623 0.06634 0.05921 0.0167 0.1448 1.0000
8.750 0.7502 0.07238 0.06545 0.0154 0.1521 1.0000
9.000 0.7308 0.07987 0.07302 0.0125 0.1628 1.0000
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Polar data table (+)
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