EH 1.0/9.0 (eh1090-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 1.0/9.0 (eh1090-il) Reynolds number: 100,000 Max Cl/Cd: 43.01 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh1090-il-100000-n5.txt Download as CSV file: xf-eh1090-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 1.0/9.0
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6209 0.08435 0.07965 -0.0070 1.0000 0.0211
-9.250 -0.6271 0.07789 0.07322 -0.0117 1.0000 0.0208
-9.000 -0.6388 0.07112 0.06644 -0.0170 1.0000 0.0206
-8.750 -0.6548 0.06582 0.06107 -0.0192 1.0000 0.0204
-8.500 -0.6668 0.06122 0.05635 -0.0197 1.0000 0.0203
-8.250 -0.6744 0.05651 0.05144 -0.0199 1.0000 0.0201
-8.000 -0.6788 0.05171 0.04635 -0.0196 1.0000 0.0201
-7.750 -0.6783 0.04720 0.04148 -0.0187 1.0000 0.0200
-7.500 -0.6741 0.04284 0.03668 -0.0175 1.0000 0.0201
-7.250 -0.6656 0.03889 0.03224 -0.0161 1.0000 0.0202
-7.000 -0.6533 0.03534 0.02816 -0.0147 1.0000 0.0205
-6.750 -0.6373 0.03234 0.02464 -0.0132 1.0000 0.0209
-6.500 -0.6205 0.02953 0.02142 -0.0120 1.0000 0.0225
-6.250 -0.6007 0.02794 0.01966 -0.0112 1.0000 0.0244
-6.000 -0.5793 0.02613 0.01758 -0.0102 1.0000 0.0263
-5.750 -0.5568 0.02419 0.01537 -0.0090 1.0000 0.0276
-5.500 -0.5342 0.02253 0.01348 -0.0079 1.0000 0.0294
-5.250 -0.5119 0.02114 0.01191 -0.0066 1.0000 0.0314
-5.000 -0.4916 0.01985 0.01063 -0.0055 1.0000 0.0360
-4.750 -0.4698 0.01895 0.00961 -0.0043 1.0000 0.0431
-4.500 -0.4498 0.01787 0.00849 -0.0030 1.0000 0.0524
-4.250 -0.4293 0.01700 0.00769 -0.0017 1.0000 0.0705
-4.000 -0.4091 0.01619 0.00700 -0.0004 1.0000 0.0973
-3.750 -0.3891 0.01546 0.00643 0.0008 1.0000 0.1344
-3.500 -0.3696 0.01474 0.00597 0.0021 1.0000 0.1844
-3.250 -0.3509 0.01399 0.00557 0.0034 1.0000 0.2576
-3.000 -0.3340 0.01317 0.00520 0.0050 1.0000 0.3652
-2.750 -0.3171 0.01227 0.00506 0.0069 0.9980 0.5274
-2.500 -0.2835 0.01176 0.00517 0.0065 0.9850 0.6996
-2.250 -0.2452 0.01172 0.00524 0.0054 0.9722 0.7858
-2.000 -0.2048 0.01179 0.00524 0.0038 0.9586 0.8408
-1.750 -0.1616 0.01191 0.00528 0.0016 0.9445 0.8819
-1.500 -0.1152 0.01204 0.00526 -0.0013 0.9295 0.9112
-1.250 -0.0639 0.01215 0.00521 -0.0053 0.9137 0.9334
-1.000 -0.0111 0.01222 0.00512 -0.0098 0.8942 0.9509
-0.750 0.0391 0.01220 0.00494 -0.0139 0.8712 0.9628
-0.500 0.0818 0.01215 0.00473 -0.0167 0.8445 0.9730
-0.250 0.1201 0.01211 0.00455 -0.0187 0.8172 0.9827
0.000 0.1587 0.01204 0.00433 -0.0208 0.7897 0.9905
0.250 0.1950 0.01198 0.00414 -0.0226 0.7631 0.9984
0.500 0.2194 0.01198 0.00403 -0.0220 0.7380 1.0000
0.750 0.2409 0.01201 0.00395 -0.0208 0.7148 1.0000
1.000 0.2624 0.01206 0.00390 -0.0196 0.6926 1.0000
1.250 0.2845 0.01213 0.00390 -0.0185 0.6710 1.0000
1.500 0.3066 0.01222 0.00390 -0.0174 0.6506 1.0000
1.750 0.3288 0.01233 0.00394 -0.0164 0.6303 1.0000
2.000 0.3510 0.01245 0.00400 -0.0153 0.6109 1.0000
2.250 0.3734 0.01259 0.00408 -0.0142 0.5923 1.0000
2.500 0.3960 0.01273 0.00422 -0.0132 0.5734 1.0000
2.750 0.4186 0.01290 0.00435 -0.0122 0.5551 1.0000
3.000 0.4412 0.01309 0.00450 -0.0112 0.5373 1.0000
3.250 0.4641 0.01327 0.00469 -0.0103 0.5185 1.0000
3.500 0.4869 0.01348 0.00493 -0.0093 0.5002 1.0000
3.750 0.5098 0.01371 0.00514 -0.0083 0.4824 1.0000
4.000 0.5329 0.01394 0.00540 -0.0074 0.4634 1.0000
4.250 0.5558 0.01419 0.00567 -0.0064 0.4443 1.0000
4.500 0.5786 0.01446 0.00596 -0.0055 0.4244 1.0000
4.750 0.6014 0.01474 0.00632 -0.0045 0.4028 1.0000
5.000 0.6241 0.01504 0.00666 -0.0036 0.3810 1.0000
5.250 0.6469 0.01537 0.00704 -0.0026 0.3600 1.0000
5.500 0.6696 0.01572 0.00746 -0.0017 0.3376 1.0000
5.750 0.6919 0.01611 0.00789 -0.0008 0.3096 1.0000
6.000 0.7131 0.01658 0.00830 0.0003 0.2694 1.0000
6.250 0.7326 0.01729 0.00882 0.0013 0.2091 1.0000
6.500 0.7508 0.01832 0.00953 0.0023 0.1412 1.0000
6.750 0.7665 0.01988 0.01064 0.0035 0.0728 1.0000
7.000 0.7825 0.02146 0.01206 0.0050 0.0450 1.0000
7.250 0.7994 0.02284 0.01349 0.0063 0.0345 1.0000
7.500 0.8162 0.02417 0.01494 0.0077 0.0295 1.0000
7.750 0.8302 0.02580 0.01670 0.0093 0.0270 1.0000
8.000 0.8461 0.02726 0.01836 0.0109 0.0253 1.0000
8.250 0.8617 0.02887 0.02020 0.0124 0.0239 1.0000
8.500 0.8777 0.03045 0.02192 0.0137 0.0220 1.0000
8.750 0.8919 0.03210 0.02365 0.0149 0.0198 1.0000
9.000 0.9038 0.03474 0.02640 0.0162 0.0184 1.0000
9.250 0.9183 0.03694 0.02889 0.0176 0.0179 1.0000
9.500 0.9304 0.03942 0.03168 0.0189 0.0175 1.0000
9.750 0.9388 0.04219 0.03479 0.0204 0.0171 1.0000
10.000 0.9423 0.04520 0.03816 0.0219 0.0168 1.0000
10.250 0.9410 0.04825 0.04153 0.0235 0.0167 1.0000
10.500 0.9330 0.05126 0.04482 0.0254 0.0166 1.0000
10.750 0.9209 0.05467 0.04849 0.0262 0.0165 1.0000
11.000 0.9080 0.05847 0.05252 0.0258 0.0166 1.0000
11.250 0.8930 0.06300 0.05726 0.0239 0.0166 1.0000
11.500 0.8759 0.06844 0.06291 0.0207 0.0166 1.0000
11.750 0.8594 0.07446 0.06909 0.0166 0.0168 1.0000
12.000 0.8415 0.08145 0.07622 0.0116 0.0169 1.0000
12.250 0.8214 0.08971 0.08459 0.0057 0.0171 1.0000
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Polar data table (+)
Polar graphs
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