Glenn Martin 4 (glennmartin4-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Glenn Martin 4 (glennmartin4-il) Reynolds number: 100,000 Max Cl/Cd: 42.8 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-glennmartin4-il-100000.txt Download as CSV file: xf-glennmartin4-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: Glenn Martin 4
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3846 0.11898 0.11506 -0.0237 1.0000 0.0885
-8.000 -0.4069 0.11702 0.11320 -0.0242 1.0000 0.0887
-7.750 -0.4297 0.11513 0.11138 -0.0237 1.0000 0.0888
-7.500 -0.3945 0.10979 0.10607 -0.0192 1.0000 0.0918
-7.250 -0.3963 0.10759 0.10393 -0.0170 1.0000 0.0939
-7.000 -0.4099 0.10551 0.10192 -0.0155 1.0000 0.0955
-6.750 -0.4300 0.10374 0.10025 -0.0138 1.0000 0.0962
-6.500 -0.4204 0.09958 0.09600 -0.0237 0.9870 0.1006
-6.250 -0.4270 0.09350 0.08964 -0.0350 0.9680 0.1040
-6.000 -0.3933 0.08920 0.08548 -0.0346 0.9606 0.1070
-5.750 -0.3726 0.08531 0.08152 -0.0376 0.9494 0.1114
-5.500 -0.3769 0.08051 0.07624 -0.0426 0.9310 0.1188
-5.250 -0.3471 0.07585 0.07178 -0.0433 0.9242 0.1224
-5.000 -0.3412 0.07290 0.06830 -0.0449 0.9069 0.1343
-4.750 -0.3045 0.06802 0.06370 -0.0468 0.9022 0.1411
-4.500 -0.2901 0.06418 0.05956 -0.0476 0.8890 0.1529
-4.250 -0.2737 0.06104 0.05616 -0.0472 0.8756 0.1683
-4.000 -0.2503 0.05758 0.05278 -0.0468 0.8636 0.1771
-3.750 -0.2327 0.05498 0.04994 -0.0459 0.8511 0.1979
-3.000 -0.1698 0.04038 0.03294 -0.0378 0.8211 0.1017
-2.750 -0.1389 0.03754 0.02966 -0.0372 0.8140 0.1015
-2.500 -0.1146 0.03525 0.02701 -0.0354 0.8029 0.1009
-2.250 -0.0753 0.03273 0.02400 -0.0359 0.7977 0.1020
-2.000 -0.0445 0.03078 0.02175 -0.0356 0.7876 0.1053
-1.750 0.0052 0.02852 0.01934 -0.0386 0.7819 0.1101
-1.500 0.0478 0.02703 0.01756 -0.0403 0.7729 0.1186
-1.250 0.1046 0.02502 0.01552 -0.0451 0.7656 0.1319
-1.000 0.4662 0.01993 0.01334 -0.1127 0.7632 1.0000
-0.750 0.5153 0.01945 0.01242 -0.1168 0.7407 1.0000
-0.500 0.5657 0.01910 0.01167 -0.1214 0.7177 1.0000
-0.250 0.6155 0.01894 0.01109 -0.1260 0.6948 1.0000
0.000 0.6529 0.01900 0.01083 -0.1281 0.6729 1.0000
0.250 0.6918 0.01915 0.01064 -0.1306 0.6522 1.0000
0.500 0.7303 0.01941 0.01057 -0.1331 0.6331 1.0000
0.750 0.7661 0.01974 0.01060 -0.1351 0.6150 1.0000
1.000 0.7955 0.02010 0.01074 -0.1358 0.5985 1.0000
1.250 0.8201 0.02047 0.01092 -0.1354 0.5825 1.0000
1.500 0.8420 0.02086 0.01116 -0.1345 0.5682 1.0000
1.750 0.8651 0.02128 0.01143 -0.1339 0.5550 1.0000
2.000 0.8938 0.02171 0.01170 -0.1345 0.5433 1.0000
2.250 0.9207 0.02214 0.01196 -0.1346 0.5319 1.0000
2.500 0.9354 0.02254 0.01235 -0.1323 0.5219 1.0000
2.750 0.9690 0.02302 0.01262 -0.1339 0.5123 1.0000
3.000 0.9775 0.02337 0.01300 -0.1302 0.5037 1.0000
3.250 1.0140 0.02389 0.01334 -0.1325 0.4958 1.0000
3.500 1.0209 0.02428 0.01382 -0.1285 0.4883 1.0000
3.750 1.0530 0.02477 0.01417 -0.1299 0.4815 1.0000
4.000 1.0674 0.02525 0.01469 -0.1275 0.4753 1.0000
4.250 1.0831 0.02567 0.01511 -0.1253 0.4687 1.0000
4.500 1.1231 0.02624 0.01555 -0.1285 0.4629 1.0000
4.750 1.1230 0.02669 0.01614 -0.1230 0.4574 1.0000
5.000 1.1419 0.02718 0.01664 -0.1216 0.4520 1.0000
5.250 1.1829 0.02778 0.01711 -0.1250 0.4472 1.0000
5.500 1.1816 0.02831 0.01780 -0.1194 0.4423 1.0000
5.750 1.1935 0.02887 0.01844 -0.1166 0.4376 1.0000
6.000 1.2203 0.02939 0.01894 -0.1170 0.4333 1.0000
6.250 1.2463 0.03008 0.01965 -0.1173 0.4290 1.0000
6.500 1.2437 0.03077 0.02051 -0.1116 0.4249 1.0000
6.750 1.2557 0.03133 0.02114 -0.1089 0.4203 1.0000
7.000 1.2844 0.03195 0.02175 -0.1097 0.4167 1.0000
7.250 1.3017 0.03268 0.02252 -0.1083 0.4126 1.0000
7.500 1.2946 0.03355 0.02360 -0.1019 0.4090 1.0000
7.750 1.3013 0.03430 0.02447 -0.0984 0.4051 1.0000
8.000 1.3263 0.03489 0.02507 -0.0985 0.4013 1.0000
8.250 1.3533 0.03564 0.02583 -0.0991 0.3974 1.0000
8.500 1.3322 0.03680 0.02725 -0.0903 0.3941 1.0000
8.750 1.3277 0.03784 0.02844 -0.0849 0.3902 1.0000
9.000 1.3476 0.03841 0.02906 -0.0840 0.3861 1.0000
9.250 1.3970 0.03894 0.02953 -0.0889 0.3822 1.0000
9.500 1.3566 0.04063 0.03151 -0.0772 0.3794 1.0000
9.750 1.3280 0.04251 0.03361 -0.0682 0.3762 1.0000
10.000 1.3248 0.04383 0.03507 -0.0638 0.3724 1.0000
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Polar data table (+)
Polar graphs
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