EPPLER 874 HYDROFOIL AIRFOIL (e874-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 874 HYDROFOIL AIRFOIL (e874-il) Reynolds number: 200,000 Max Cl/Cd: 49.66 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e874-il-200000-n5.txt Download as CSV file: xf-e874-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 874 HYDROFOIL AIRFOIL
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 -0.6023 0.08275 0.07935 -0.0103 1.0000 0.0077
-9.000 -0.6100 0.07695 0.07361 -0.0136 1.0000 0.0076
-8.750 -0.6203 0.07021 0.06693 -0.0180 1.0000 0.0075
-8.500 -0.6308 0.06362 0.06036 -0.0237 1.0000 0.0072
-8.250 -0.6452 0.05569 0.05229 -0.0275 1.0000 0.0071
-8.000 -0.6552 0.05010 0.04647 -0.0284 1.0000 0.0070
-7.750 -0.6614 0.04500 0.04107 -0.0278 1.0000 0.0070
-7.500 -0.6621 0.04059 0.03630 -0.0265 1.0000 0.0070
-7.250 -0.6588 0.03654 0.03182 -0.0246 1.0000 0.0070
-7.000 -0.6514 0.03295 0.02776 -0.0224 1.0000 0.0071
-6.750 -0.6381 0.03045 0.02484 -0.0205 1.0000 0.0077
-6.500 -0.6222 0.02863 0.02258 -0.0186 1.0000 0.0084
-6.250 -0.6106 0.02518 0.01869 -0.0164 1.0000 0.0090
-6.000 -0.5932 0.02296 0.01613 -0.0146 1.0000 0.0092
-5.750 -0.5739 0.02114 0.01397 -0.0129 1.0000 0.0092
-5.500 -0.5540 0.01953 0.01216 -0.0113 1.0000 0.0093
-5.250 -0.5338 0.01813 0.01059 -0.0097 1.0000 0.0095
-5.000 -0.5137 0.01693 0.00925 -0.0081 1.0000 0.0097
-4.750 -0.4934 0.01590 0.00809 -0.0065 1.0000 0.0101
-4.500 -0.4723 0.01506 0.00711 -0.0051 1.0000 0.0105
-4.250 -0.4505 0.01435 0.00625 -0.0038 1.0000 0.0112
-4.000 -0.4281 0.01372 0.00545 -0.0026 1.0000 0.0127
-3.750 -0.4055 0.01312 0.00465 -0.0013 1.0000 0.0166
-3.500 -0.3863 0.01195 0.00395 0.0001 1.0000 0.0971
-3.250 -0.3661 0.01123 0.00379 0.0011 1.0000 0.2005
-3.000 -0.3437 0.01089 0.00358 0.0021 1.0000 0.2400
-2.750 -0.3138 0.01062 0.00334 0.0015 0.9971 0.2707
-2.500 -0.2771 0.01032 0.00310 -0.0006 0.9895 0.3078
-2.250 -0.2432 0.01000 0.00286 -0.0021 0.9792 0.3529
-2.000 -0.2130 0.00966 0.00266 -0.0027 0.9641 0.4012
-1.750 -0.1810 0.00930 0.00248 -0.0037 0.9487 0.4585
-1.500 -0.1463 0.00889 0.00232 -0.0051 0.9322 0.5357
-1.250 -0.1093 0.00845 0.00217 -0.0070 0.9116 0.6243
-1.000 -0.0679 0.00798 0.00206 -0.0095 0.8864 0.7340
-0.750 0.0105 0.00770 0.00212 -0.0198 0.8612 0.8785
-0.500 0.0902 0.00777 0.00205 -0.0306 0.8196 0.9361
-0.250 0.1326 0.00798 0.00205 -0.0334 0.7735 0.9629
0.000 0.1666 0.00821 0.00209 -0.0345 0.7353 0.9841
0.250 0.2086 0.00837 0.00208 -0.0376 0.7013 0.9964
0.750 0.2628 0.00861 0.00205 -0.0373 0.6464 1.0000
1.000 0.2863 0.00873 0.00207 -0.0364 0.6236 1.0000
1.250 0.3099 0.00886 0.00215 -0.0355 0.6043 1.0000
1.500 0.3338 0.00899 0.00223 -0.0347 0.5862 1.0000
1.750 0.3579 0.00912 0.00232 -0.0339 0.5694 1.0000
2.000 0.3821 0.00926 0.00244 -0.0331 0.5545 1.0000
2.250 0.4064 0.00940 0.00259 -0.0323 0.5406 1.0000
2.500 0.4308 0.00956 0.00280 -0.0315 0.5271 1.0000
2.750 0.4552 0.00972 0.00299 -0.0308 0.5134 1.0000
3.000 0.4793 0.00989 0.00320 -0.0299 0.4974 1.0000
3.250 0.5021 0.01011 0.00338 -0.0288 0.4667 1.0000
3.500 0.5207 0.01057 0.00343 -0.0270 0.3668 1.0000
3.750 0.5307 0.01252 0.00402 -0.0246 0.0837 1.0000
4.000 0.5489 0.01368 0.00487 -0.0228 0.0173 1.0000
4.250 0.5711 0.01427 0.00564 -0.0215 0.0141 1.0000
4.500 0.5923 0.01497 0.00650 -0.0200 0.0125 1.0000
4.750 0.6123 0.01583 0.00749 -0.0184 0.0115 1.0000
5.000 0.6277 0.01736 0.00913 -0.0162 0.0097 1.0000
5.250 0.6495 0.01795 0.00981 -0.0150 0.0083 1.0000
5.500 0.6688 0.01909 0.01106 -0.0132 0.0075 1.0000
5.750 0.6882 0.02048 0.01263 -0.0115 0.0072 1.0000
6.000 0.7082 0.02206 0.01437 -0.0098 0.0069 1.0000
6.250 0.7281 0.02387 0.01640 -0.0082 0.0067 1.0000
6.500 0.7474 0.02594 0.01876 -0.0064 0.0067 1.0000
6.750 0.7652 0.02835 0.02152 -0.0044 0.0067 1.0000
7.000 0.7807 0.03107 0.02464 -0.0022 0.0068 1.0000
7.250 0.7934 0.03415 0.02813 0.0002 0.0069 1.0000
7.500 0.8034 0.03743 0.03180 0.0027 0.0071 1.0000
7.750 0.8104 0.04088 0.03562 0.0051 0.0073 1.0000
8.000 0.8139 0.04458 0.03966 0.0076 0.0075 1.0000
8.250 0.8148 0.04814 0.04352 0.0098 0.0078 1.0000
8.500 0.8119 0.05182 0.04746 0.0118 0.0079 1.0000
8.750 0.8038 0.05567 0.05155 0.0137 0.0081 1.0000
9.000 0.7916 0.05909 0.05513 0.0157 0.0082 1.0000
9.250 0.7755 0.06241 0.05858 0.0169 0.0083 1.0000
9.500 0.7583 0.06682 0.06312 0.0152 0.0083 1.0000
9.750 0.7429 0.07237 0.06877 0.0109 0.0084 1.0000
10.000 0.7262 0.08026 0.07673 0.0046 0.0084 1.0000
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Polar data table (+)
Polar graphs
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