XFOIL Version 6.96 Calculated polar for: RAF 30 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.000 -0.7279 0.10867 0.10473 -0.0199 1.0000 0.0491 -13.750 -0.7197 0.10703 0.10310 -0.0197 1.0000 0.0497 -13.500 -0.9410 0.06599 0.06111 -0.0481 1.0000 0.0407 -13.250 -0.9636 0.06193 0.05684 -0.0487 1.0000 0.0405 -13.000 -0.9843 0.05776 0.05248 -0.0482 1.0000 0.0407 -12.750 -1.0018 0.05457 0.04908 -0.0467 1.0000 0.0407 -12.500 -1.0170 0.05133 0.04562 -0.0445 1.0000 0.0408 -12.250 -1.0273 0.04853 0.04263 -0.0417 1.0000 0.0410 -12.000 -1.0323 0.04587 0.03983 -0.0390 1.0000 0.0415 -11.750 -1.0362 0.04357 0.03735 -0.0358 1.0000 0.0417 -11.500 -1.0335 0.04144 0.03505 -0.0334 1.0000 0.0423 -11.250 -1.0262 0.03949 0.03297 -0.0313 1.0000 0.0430 -11.000 -1.0185 0.03776 0.03108 -0.0291 1.0000 0.0440 -10.750 -1.0105 0.03607 0.02918 -0.0268 1.0000 0.0451 -10.500 -1.0013 0.03443 0.02730 -0.0244 1.0000 0.0462 -10.250 -0.9900 0.03283 0.02544 -0.0222 1.0000 0.0471 -10.000 -0.9770 0.03143 0.02378 -0.0201 1.0000 0.0478 -9.750 -0.9581 0.02898 0.02121 -0.0192 1.0000 0.0492 -9.500 -0.9393 0.02764 0.01989 -0.0181 1.0000 0.0510 -9.250 -0.9215 0.02653 0.01872 -0.0167 1.0000 0.0526 -9.000 -0.9030 0.02542 0.01751 -0.0152 1.0000 0.0541 -8.750 -0.8845 0.02441 0.01640 -0.0137 1.0000 0.0557 -8.500 -0.8664 0.02364 0.01550 -0.0121 1.0000 0.0571 -8.250 -0.8495 0.02213 0.01407 -0.0105 1.0000 0.0594 -8.000 -0.8334 0.02127 0.01322 -0.0086 1.0000 0.0615 -7.750 -0.8174 0.02049 0.01242 -0.0066 1.0000 0.0637 -7.500 -0.8013 0.01982 0.01169 -0.0045 1.0000 0.0663 -7.250 -0.7883 0.01892 0.01082 -0.0020 1.0000 0.0694 -7.000 -0.7745 0.01823 0.01015 0.0004 1.0000 0.0732 -6.750 -0.7597 0.01764 0.00952 0.0028 1.0000 0.0778 -6.500 -0.7482 0.01687 0.00884 0.0056 1.0000 0.0846 -6.250 -0.7363 0.01617 0.00823 0.0083 1.0000 0.0974 -6.000 -0.7277 0.01526 0.00754 0.0116 1.0000 0.1306 -5.750 -0.7192 0.01444 0.00700 0.0147 1.0000 0.1770 -5.500 -0.7089 0.01384 0.00667 0.0175 1.0000 0.2238 -5.250 -0.6969 0.01343 0.00645 0.0201 1.0000 0.2688 -5.000 -0.6846 0.01309 0.00628 0.0225 1.0000 0.3082 -4.500 -0.6282 0.01246 0.00601 0.0211 0.9925 0.3999 -4.250 -0.5903 0.01217 0.00592 0.0187 0.9854 0.4514 -4.000 -0.5530 0.01195 0.00585 0.0166 0.9778 0.4972 -3.750 -0.5134 0.01180 0.00580 0.0141 0.9712 0.5385 -3.500 -0.4786 0.01165 0.00575 0.0127 0.9623 0.5739 -3.250 -0.4375 0.01154 0.00570 0.0101 0.9568 0.6050 -3.000 -0.4031 0.01141 0.00561 0.0089 0.9477 0.6285 -2.750 -0.3608 0.01128 0.00549 0.0062 0.9426 0.6507 -2.500 -0.3246 0.01117 0.00544 0.0047 0.9345 0.6718 -2.250 -0.2851 0.01108 0.00537 0.0028 0.9282 0.6973 -2.000 -0.2491 0.01098 0.00533 0.0016 0.9198 0.7164 -1.750 -0.2110 0.01085 0.00521 -0.0001 0.9119 0.7321 -1.500 -0.1784 0.01075 0.00511 -0.0007 0.9009 0.7467 -1.250 -0.1428 0.01064 0.00501 -0.0018 0.8907 0.7600 -1.000 -0.1106 0.01054 0.00492 -0.0021 0.8779 0.7728 -0.750 -0.0825 0.01049 0.00486 -0.0016 0.8636 0.7856 -0.500 -0.0553 0.01046 0.00483 -0.0010 0.8500 0.7988 -0.250 -0.0285 0.01044 0.00480 -0.0004 0.8370 0.8124 0.000 0.0000 0.01044 0.00480 0.0000 0.8248 0.8248 0.250 0.0285 0.01044 0.00480 0.0004 0.8124 0.8370 0.500 0.0553 0.01046 0.00483 0.0010 0.7988 0.8500 0.750 0.0825 0.01049 0.00486 0.0016 0.7856 0.8636 1.000 0.1106 0.01054 0.00492 0.0021 0.7728 0.8779 1.250 0.1428 0.01064 0.00501 0.0018 0.7601 0.8907 1.500 0.1784 0.01075 0.00512 0.0007 0.7467 0.9009 1.750 0.2111 0.01085 0.00521 0.0001 0.7320 0.9119 2.000 0.2491 0.01098 0.00534 -0.0016 0.7166 0.9198 2.250 0.2850 0.01107 0.00537 -0.0028 0.6971 0.9282 2.500 0.3245 0.01116 0.00543 -0.0047 0.6718 0.9345 2.750 0.3609 0.01128 0.00549 -0.0062 0.6509 0.9426 3.000 0.4031 0.01142 0.00561 -0.0089 0.6285 0.9477 3.250 0.4376 0.01154 0.00570 -0.0101 0.6049 0.9568 3.500 0.4787 0.01165 0.00574 -0.0127 0.5734 0.9624 3.750 0.5133 0.01180 0.00580 -0.0141 0.5385 0.9711 4.000 0.5531 0.01195 0.00585 -0.0166 0.4973 0.9778 4.250 0.5904 0.01217 0.00592 -0.0187 0.4514 0.9854 4.500 0.6283 0.01246 0.00601 -0.0212 0.3996 0.9926 4.750 0.6675 0.01280 0.00612 -0.0240 0.3472 0.9991 5.000 0.6844 0.01309 0.00627 -0.0225 0.3071 1.0000 5.250 0.6968 0.01343 0.00645 -0.0200 0.2683 1.0000 5.500 0.7088 0.01384 0.00667 -0.0175 0.2238 1.0000 5.750 0.7190 0.01444 0.00701 -0.0147 0.1764 1.0000 6.000 0.7276 0.01526 0.00755 -0.0116 0.1302 1.0000 6.250 0.7362 0.01617 0.00823 -0.0083 0.0974 1.0000 6.500 0.7481 0.01687 0.00884 -0.0055 0.0845 1.0000 6.750 0.7596 0.01764 0.00952 -0.0027 0.0778 1.0000 7.000 0.7744 0.01823 0.01015 -0.0004 0.0732 1.0000 7.250 0.7882 0.01893 0.01083 0.0020 0.0694 1.0000 7.500 0.8012 0.01983 0.01170 0.0045 0.0664 1.0000 7.750 0.8175 0.02049 0.01242 0.0066 0.0638 1.0000 8.000 0.8334 0.02127 0.01322 0.0086 0.0615 1.0000 8.250 0.8495 0.02212 0.01406 0.0105 0.0595 1.0000 8.500 0.8665 0.02365 0.01551 0.0120 0.0571 1.0000 8.750 0.8846 0.02443 0.01641 0.0137 0.0557 1.0000 9.000 0.9031 0.02544 0.01753 0.0152 0.0541 1.0000 9.250 0.9215 0.02652 0.01870 0.0167 0.0525 1.0000 9.500 0.9393 0.02762 0.01987 0.0181 0.0509 1.0000 9.750 0.9582 0.02899 0.02122 0.0192 0.0493 1.0000 10.000 0.9772 0.03145 0.02380 0.0200 0.0479 1.0000 10.250 0.9903 0.03283 0.02543 0.0221 0.0471 1.0000 10.500 1.0014 0.03443 0.02730 0.0244 0.0462 1.0000 10.750 1.0105 0.03611 0.02923 0.0268 0.0451 1.0000 11.000 1.0186 0.03778 0.03110 0.0291 0.0440 1.0000 11.250 1.0267 0.03947 0.03294 0.0312 0.0430 1.0000 11.500 1.0332 0.04147 0.03509 0.0334 0.0423 1.0000 11.750 1.0357 0.04364 0.03743 0.0359 0.0418 1.0000 12.000 1.0315 0.04592 0.03989 0.0391 0.0416 1.0000 12.250 1.0274 0.04837 0.04249 0.0418 0.0411 1.0000 12.500 1.0161 0.05122 0.04554 0.0446 0.0409 1.0000 12.750 1.0025 0.05453 0.04904 0.0466 0.0407 1.0000 13.000 0.9847 0.05829 0.05299 0.0480 0.0405 1.0000 13.250 0.9627 0.06245 0.05737 0.0485 0.0404 1.0000 13.500 0.9392 0.06604 0.06119 0.0479 0.0408 1.0000 13.750 0.6283 0.09894 0.09524 0.0262 0.0498 1.0000 14.000 0.6277 0.10251 0.09881 0.0251 0.0491 1.0000